Title of Invention

METALLIC CELLULAR STRUCTURE

Abstract A honeycomb structure comprising a plurality of abutting semi-hexagonal corrugated metal strips brazed to a metal backplate, each corrugated metal strip having alternating flat slanted sides interconnected by a flat crest, the abutting strips joined together at adjacent flat crests by welding to form generally hexagonal cells, the slanted sides having an equal length and the crests having a length greater than the slanted sides whereby the cell width w measured between opposed flat crests of adjacent strips relative to the distance b between the planes of opposed slanted sides has a ratio of b:w of greater than 1.15:1.0.
Full Text FORM 2
THE PATENTS ACT 1970
[39 OF 1970]
COMPLETE SPECIFICATION
[See Section 10, Rule 13]
"METALLIC CELLULAR STRUCTURE"
NEOMET LIMITED, a company organized under the laws of England, having its principal office or place of business at 92 Cross Lane, Marple, Stockport, SK6 7PZ, United Kingdom,
The following specification particularly describes tne nature ot tne invention and the manner in which it is to be performed:-


METALLIC CELLULAR STRUCTURE
Background of the Invention
(i) Field of the Invention
The present invention relates to abradable gas turbine seals and, more particularly, lo novel turbine seals having cellular metallic structures suitable for operation in an oxidizing and/or carburizing gas environment at high temperatures.
(ii) Description of the Related Art
Cellular structures made from thin sheet metal or metal foil are attractive for use in space and aerospace applications, in particular in jet engines, because they provide a high stffness to weight ratio and high mechanical energy absorption capabilities and acoustic damping while being light in weight. As a direct consequence of the low density they are also readily abradable, which characteristic is used in jet engines, and also in stationary gas turbines used for power generation, to reduce the gap between the stationary shroud and rotating blade components, thereby improving efficiency of the gas turbine cycle. While the cellular structure used as an abradable seal must be soft enough to allow the tips or knife edges of a rotating blade to cut into it without causing damage to the blade and the structure carrying the abradable cellular structure, it must be strong enough to withstand static and high frequency vibratory loads, abrasion, cyclic thermal stresses and cyclic oxidation and/or carburization attack, alloccuring at high temperatures. Furthermore, the seal must not crack under thermal shock and low cycle fatigue loading. In other words, the cellular structure used as a gas path seal must be resistant to hot gas corrosion attack and must have excellent structural integrity and long term dimensional stability to withstand the mechanical and thermal loads imposed on it for many cycles and over lengthy periods of time.
Conventional abradable cellular gas pathseals are manufactured from highly alloyed, austenitic stainless steels and nickel-base alloys, and are provided having regular hexagonal cells formed by corrugating ribbons of sheet or foil and welding the corrugated sheets together where abutting walls of adj acent corrugated ribbons meet to form a double wall, i.e. a node.
U.S. Patent No. 3,867,061 issued February 18,1975 typifies a conventional prior art honeycomb shroud for rotor blades for turbines in which the honeycomb cell walls are made

from nickel-base heat-resistant alloys and the honeycomb strips are brazed or resistance welded to a back-up ring.
U.S. Patent No. 4063,742 issued December 20,1977 discloses another embodiment of prior art abradable fluid seal for use in gas turbines consisting of a conventional honeycomb made by conventional honeycomb equipment in which abutting three-sided semi-hexagonal strips each having a pair of fiat slanted sides and a flat crest of equal length standing on edge ("soe") are resistance welded together at the crests.
Honeycomb structures typically are fabricated by building up the structure layer by layer to result in a three dimensional body having a height determined by the width to which the ribbon had been slit prior to corrugation. The length of the structure is parallel to the plane of the double walls or nodes and the width is represented by the direction of layer build up. Such a cellular body is brazed to face sheets to form a sandwich skin or brazed to backplates of a ring or ring segments to form a seal, the contacting surface of the cellular body being a "soe" surface. Such brazing does not only join the cellular structure body to the face sheet or backplate but also contributes significantly to the stiffness of the cellular structure itself This is due to the fact that the brazing alloy, in a liquid state and due to capillary action, rises up the gap formed by the two neighbouring walls of the node, thereby wetting the abutting surfaces of said node walls and, after resolidification of the braze filler metal, forms a stiffened ceEular structure. The braze flow up the nodal walls is referred to as "wicking". Such wicking is essential to provide a brazed cellular structure with good mechanical behaviour at high temperatures to resist combined thermal and mechanical loads.
The most commonly used method to provide a turbine engine seal segment or ring is to sandwich a braze filler metal foil, tape or brazing powder between the abutting surfaces of the "soe" cellular structure and the backplate surface, and brazing this assembly together. The liquid braze metal must travel up the full depth of the nodes to impart improved structural strength. The exposed surface at which the rotor blade tip or knife edge rubs is also the surface where the most severe combination of mechanical load, wear and temperature occurs and therefore requires excellent structural integrity. If inadequate wicking success is achieved during brazing, there is a twofold drawback: not only is the cellular structure unstifTened, with the consequence oflow shape stability, which may cause premature failure of the seal body in service, but also the bulk of the braze filler metal

remains at the backplate surface and penetrates both the backplate material and the cellular foil alloy structure by diffusion while in the liquid state to a much larger extent than would be the case if the braze alloy flowed up the nodes. This has the effect of significantly altering the chemical and mechanical characteristics of the backplate and the foil metal alloy, at least locally at their juncture.
Because oxidation resistance and carburization resistance at high temperatures are required, sheet or foil metals having a good hot gas corrosion resistance must be used for the manufacture of turbine seals. The resistance of metals to oxidation and carburization is based on the formation of surface oxide layers which protect the underlying metal from further attack. The nickel base alloys and highly alloyed, austenitic stainless steels used in conventional abradable cellular seals rely on the formation of chromia (Cr203) or mixed Cr203 / NiO oxides to provide such protection. At very high temperatures or in combustion gas atmospheres flowing at high speeds, both found in turbine engines, this type of protection is unstable due to further oxidation o fthe Cr203 to volatile CrOj as described by James L. Smialek and Gerald H. Meier in Superalloys II by Chester T. Sims et al. (eds.), John Wiley & Sons, Inc. (1987). The same authors, in the same handbook, describe that much better protection is achieved'with alumina (Al2O3) which is formed onmetals having a high Al concentration and being further enhanced by high chromium (Cr) contents and the addition of rare earth metals, such as yttrium (Y), zirkoniuin (Zr), cerium (Ce), hafnium (Hf), ytterbium (Yb), praseodymium (Pi), neodymium (Nd), samarium (Sm) or lanthanum (La) leading to so called JVTCrAlX alloys with X representing the rare earth metal addition and M being die major alloy constituent selected from the group of Ni, Fe or Co or combinations thereof. If yttrium is chosen as the main rare earth addition, then the resulting alloys are referred to as MCrAlY alloys. MCrAlY alloys are disclosed in U.S. Pat. No. 5,116,690 by WJ. Brindley et aL, issued May 26,1992. Other patents such as U.S. Pat No. 4,034,142 issued July 5,1977 to R. J. Hecht and U.S. Pat No. 4,503,122 issued March 5, 1985 to A R. NichoIIs describe similar MCrAlY alloys with excellent self protection against hot gas attack. All the aforementioned patents describe the use ofMCrAlY alloys as overlay coatings and not as a structural material in the form of foil to provide a welded cellular structure.
It is difficult to obtain MCrAlY alloys in thin sheet or foil form because they are hard

and difficult to roll which is the effect of the high aluminiurn concentration, typically in the range 2-6% by weight, with 6 - 7 % representing the upper limit to retain workability. If available in thin sheet or foil form the MCrAIY materials are difficult to corrugate and to form into a cellular structure such as described above. In particular, these materials are difficult to form into a corrugated ribbon, if aportion or all of the added yttrium is present as yttria (Y2O3) and/or part of the alloy matrix alutninium is present as matrix alumina. The insufficient formability of these alloys results in cellular structures which may deviate significantly from the optimum shape since no sharp comers, but only rounded ones with a relatively large bend radius, can be achieved by corrugations which compromises brazeablity. This is especially true for MCrAIY foil or sheet metal having thick gauges. For use at high temperatures, the foil thickness of the MCrAIY sheet or foil used must be greater than a certain minimum limit to avoid break-away oxidation. Break-away or catastrophic oxidation occurs when, due to straightforward growth of the protective alumina scale or due to repeated scale spallation and automatic rebuild of the protective scale in oxidising environments at high temperature, trie bulk aluininium concentration in the foil or sheet alloy is consumed and falls below a certain critical value. This phenomenon is described by W. Quadakkers and K. Bongartz in Werkstqffe and Korrosion 45,232 - 241 (1994). The same authors propose to use high initial Al concentrations in the MCrAIY alloy and the use of trucker foil or sheet to delay the onset of break-away oxidation. Both of these measures, however, are detrimental to formability and to brazeability of the material when formed into a cellular structure and brazed to a backing sheet metal riDg, sheet metal ring segments or cast backing members.
Even if successfully formed into a cellular shape with good geometrical features, the MCrAIY materials are difficult to braze because they contain a high amount of Al and Y or Y303. Due to the high affinity of alurninium to oxygen, there is a strong tendency towards the formation of stable and tightly adherent alumina scales at the MCrAIY metal surface, thereby reducing the wettability and consequently braze wicking which is required to achieve structural stiffness of the cellular structure to be used as an abradable turbine engine seal Likewise yttrium has a very strong affinity to oxygen to form very stable yttria (Y203) which also acts as a braze flow stopper. Typically therefore MCrAIY alloys, typically containing 6 - 30 % by weight Cr, 2 - 7 % by weight Al, 0.005 - 0.6 % by weight Y and

other reactive elements from the group consisting of Zr, Ti, Hf, La, Ce, Er, Yb, Pr, Nd, Sm, balance one or more of the elements belonging to the group of Fe, Ni, Co are extremely difficult to braze and it is therefore difficult to use them in a cellular structure of an abradable seal system.
H. Bode in "Metal-Supported Automotive Catalytic Converters", H. Bode (ed.), Werkstoff ifomnationsgesellschaft mbH, Frankfurt (1997), p. 17 - 31, describes cellular structures made from MCrAlY foil alloys for use at high temperature as support structures for automotive catalysts. The cellular structures are built up by alternating layers of flat or microcorrugated foil and corrugated foil having sinusoidal ridges. The sinusoidal corrugated foil may be manufactured using Fe - Cr - Al - Y alloys.
PCT ApplicationNo. PCT/EP95/008S5 (WO 95/26463) published March 9,1995, discloses a metallic cellular structure made from an MCrAlY alloy having an aluminium content of greater than 6 % by -weight for increased electrical resistivity. The cellular structure is fabricated by extrusion of metal powders or metal - ceramic powders or by making the metal foil by rapid solidification because of the difficulties in fonnability of MCrAlY alloys having an aluminum content of greater man 6 wt%.
Summary of the Invention
In accordance with the present invention there are provided novel cellular structures preferably made from MCrAlY alloy metal foil or sheet having good structural integrity and stiffness after brazing to a metal backing structure and therefore show long term dimensional stability at high temperature.
m its broadest form mis is achieved through a novel, elongated cell shape of a cellular honeycomb structure. According to the present invention, the cell shape is elongated in the direction parallel to the direction of the double wall crests or nodes and, more particularly, comprises a plurality of abutting semi-hexagonal strips each having alternating flat slanted sides interconnected by a flat crest, the abutting strips joined together at the adjacent flat crests to form generally hexagonal cells having double wall crests or nodes, the slanted sides having an equal length and the crests having a length greater than the slanted sides whereby the width w measured between opposed flat crests of adjacent strips relative to the distance b between the planes of opposed slanted sides has a ratio of brw of greater

than 1.15:1.0. Preferably, the ratio ofbrwis 1.2 to 2.0:1.0, and more preferably, the ratio of b:wis 1.3 to 1.6:1.0.
In a further preferred embodiment of the invention, the semi-hexagonal elongate strips are a foil metal or sheet metal alloy of a MCrAlY comprising 13 to 27% by weight Cr, 2 to 7% by weight Al, 0.005 to 0.6% by weight Y, at least one of up to 0.6% by weight Zr, up to 0.6% by weight Hf up to 0.6% by weight Ce, up to 6% by weight La, up to 6% by weight Si, up to 0.6% by weight Mn, up to 0.6% by weight Ti and up to 0.3% by weight C, and the balance, apart from impurities, Fe or Ni or combinations thereof More preferably, the iron content is at least 6% by weight Fe, the balance Fe or Ni or combinations thereof
The novel honeycomb structure of the invention, can be used as an abradable seal in a gas turbine such as a jet engine or stationary gas turbine comprising a metal backplate with the honeycomb structure attached standing on edge to the metal backing plate, the honeycomb structure consisting of the metal foil or sheet metal of the MCrAlY. The metal back member preferably is a nickel-base alloy in the form of a backing sheet metal ring, sheet metal ring segments or cast backing members and the metal foil or sheet metal used to manufacture the cellular structure has a thickness of 0.100 mm to 0.400 mm.
Brief Description of the Drawings
The abradable gas seal of the invention will now be described with reference to the accompanying drawings, in which:
Figure 1 is a plan view of a prior art honeycomb cellular structure;
Figure 2 is a plan view of the novel honeycomb cellular structure of the
present invention,"
Figure 3 is a perspective view of a honeycomb cellular structure of the
invention; and
Figure 4 is a perspective view of the honeycomb structure of the invention
illustrated in Figures 2 and 3 preparatory to attachment by brazing to
a backplate.
Description of the Preferred Embodiments
Referring to the drawings, Figure 1 illustrates a prior art honeycomb cellular

structure 10 fabricated from a plurality of strips 12 of corrugated metal foil or sheet metal having a three-sided, semi-hexagon shape consisting of a pair of flat slanted sides 14,16 having a length k interconnected by adjacent intermediary flat crests 18,19 having a length m, all of equallength wherein m = k. The adjacent strips 12,12a, 12b are joined together at their abutting crests 18,19 such as by resistance welding or by laser spot welding to form the three-dimensional body 10 having a height determined by the width to which the strips had been slit from a sheet, not shown.
Honeycomb cellular structure 10 has a long axis parallel to the direction depicted by I peipendicular to the cell with the distance hstween the planes of opposed slanted sides 14,14 and 16,16 of adjacent strips 12,12a, 12b is equal to the distance w, i.e. b.w = 1.
Turning now to Figure 2, the honeycomb cellular structure 30 of the present invention fabricated from a plurality of corrugated strips 32 of metal mil or sheet metal each having a three-sided shape consisting of a pair of flat slanted sides 34,36 having an equal lengthkinterconnected by adjacent intermediary flat crests 38,39 having a length m wherein m is)longer thankr-whereby the cell with whenmeasured between opposed flat crests 18,
—_
19 of adjacent strips is shorter than the distance b befoeen the planes of opposed slanted sides 34,34 and 36,36, the ratio b:w being at least 1.15:1.0, preferably 1.2 to 2.0:1.0, and more preferably 1.3 to 1.6:1.0. Alternatively, with reference to the length of cell y, as viewed in Figures 1 and 2, relative to the width of cll w the ratio y/w n\ust be at least 2.30:1.0. The ratio of y:w in Figure 1 is 1.155:1.0.
It has been found surprisingly that the honeycomb cellular structure having a ratio of b w of greater than 1.15:1.0, preferably, 1.2:1.0 to 2.0:1.0, and more preferably 1.3:1.0 to 1.6:1.0, provides consistently good braze wickingofup to 100% for honeycomb cellular structures made from the MCrAlVs of the invention. The adjacent strips 32,32a, 32b are joined together at their abutting crests 3 8,39 such as by resistance welding or by laser spot welding 40 to form mree-dimensional body 3 0 shown in Figures 3 and 4 having a height H determined by the width of the strips, a length L and width B. The honeycomb structure 30 standing on edge with surface 42 abutting surface 44 of backplate 46 of a ring shroud (not shown) is brazed to a backplate 46 of a ring shroud to form a seal structure for use as an abradable turbine seal. Backplate 46 may be a backing sheet metal ring, sheet metal ring

segments or cast backing members of a nickel-base alloy forming part of the shroud of the gas turbine of a jet engine or a stationary gas turbine.
The preferred metal foil or sheet alloy of the invention consists of 6 to 30% by
. weight Cr, 2 to 7% by weight Al, 0.005 to 0.6% by weight Y, at least one of the elements
selected from the group consisting of Zr, Hf, Ce, La, Si, Mn, Ti in the amount of at least
0.6% by weight and C in the amount of 0.3% by weight, at least 6% by weight Fe, and the
balance, apart from impurities, being Fe or Ni or combinations thereof.
The honeycomb cellular structure 30 is attached to backplate 46 by resistance welding or laser spot welding. A braze filler metal in powder form then is applied by filling the vertically aligned cells with the braze powder and the assembly heated to above the melting point of the braze powder, preferably in the range of about 1190°C to 1215°C iu a conventional vacuum furnace for a time sufficient such as about 2 to 8 minutes to melt and wet the nodal walls of the honeycomb cellular structure and to rise up the double nodal walls by capillary action to effectively join the structure to the backplate and to stiffen the honeycomb cellular structure. Suitable cobalt-base braze filler metal alloys for theMCrAlY honeycomb structure can consist of 19% by weight Cr, 17% by weight Ni, 8% by weight Si, Wo by weight W, 0.8% by weight B, 0.4% by weight C and the balance Co, or 21% by weight Cr, 4.5% by weight W, 2.4% by weight B, 1.6% by weight Si, 0.1 % by weight C, and the balance Co.
The abradable turbine seal of the invention will now be described with reference to the following non-limitative examples.
EXAMPLE 1;
A conventional, non MCrAlY alloy having the nominal chemical composition of 22% by weight Cr, 18% by weight Fe, 9% by weight Mo, 1.5% by weight Co, 0.6% by weight W, balance Ni was provided in the form of 125 pm (0.125 mm, 0.005" ) thick foil to fonn a cellular structure illustrated in Figure 1 having a length L of 55 trrm; a width B of 35 mm and anodal height H of 8 mm, by corrugating and laser spot welding the foil to form a six-sided honeycomb cell shape having a nodal cell size as measured as the minimum internal distance between the cell walls forming the nodal walls of w = 1,59 mm and a cell size b, measured as the minimum internal distance between opposed single foil thickness

cell walls, of 1.59 mm. Therefore the ratio of brw is 1. Small deviations, usually less than 10%, from this value are allowable due to manufacturing tolerances. The structure, having the described cellular configuration, was brazed to a metallic backplate as typified in Figure 4 using a braze filler metal in powder form having the chemical composition of 19% by weight Cr, 10.2% by weight Si, 0.03% by weight C, balance Ni. The braze alloy powder was appUed by filling a total of 8.7 ginto the cells after having resistance welded the cellular body to the backplate with the nodal height dimension H standing on edge at 90" to the backplate. This assembly was heated to 1193 °C and held at that temperature for 6 minutes in a conventional vacuum furnace causing the braze filler metal to melt and wet the nodal walls of the cellular structure and to join me cellular structure to the backplate. After brazing, the braze wicking result was determined by assessing the percentage of nodes which showed complete wetting with braze filler over the total nodal height of 8 mm, i.e. the percentage of nodes showing braze filler metal at the surface 49 (Figure 4). This result was assessed to be 100% with a total of 114 nodes investigated.
EXAMPLE 2:
An MCrAIY alloy foil having a thickness of 110 /an (0.110 mm, 0.004") with an alloy composition of 20.2% by weight Cr, 5.8% by weight AL 0.05% by weight Y, 0.04% by weight Zr, 0.04% by weight Hf, balance Fe, was formed into two cellular structures having the same outside dimensions and cell sizes as described in Example 1. The two structures were resistance welded to the same backplate material as used in Example 1 and the same type and amount ofbraze filler metal as used in Example 1 was filled into the cells. The assemblies were brazed in the same furnace run as the assembly of Example 1. The braze wicking results, assessed as described in Example 1, were 54 and 71% respectively. A total of 114 and 95 nodes, respectively, were investigated.
A comparison of the results of examples 1 and 2 suggests that a much better braze wicking result is achieved with conventional Ni-base alloys than with MCrAIY alloys when a conventional honeycomb cell shape is used.
EXAMPLE 3:
An MCrAIY alloy having the nominal chemical composition of 19% by weight Cr,

5.5% by weight Al, 0.5% by weight Ti, 0.21 % by weight Y and balance Fe was provided in thefoimofafoilhavmgathicknessof0.l25mm(O1.25min, 0.005")- This foil material was corrugated and welded to provide a cellular structure body having outside dimensions as given in Example l,i.e, a length Lof55 mm, a width Bof35 mm and a nodal height H of 8 mm. The cell size ofme cellular slructure of this body was w=2.5mmandb =2.5 mm when assessed as described in Example 1. The cellular structure was resistance welded to a backplate material as used in Examples 1 and 2 with the nodal height dimension H standing on edge being at 90° to the backplate. Braze filler metal powder having the nominal chemical composition of 19% by weight Cr, 17% by weight Ni, 8% by weight Si, 4% by weight W, 0.8% by weight B, 0.4% by weight C and balance Co was filled into the cells of the cellular structure. The same amount of braze filler metal as in Example 1 was used. Theassembly was heated toa temperature of 1204°C and held at mat temperature for 6 minutes. This treatment caused the braze filler metal to melt and wick up the nodal walls. The braze wicking success, assessed as outlined in Example 1, was only 8% with, a total of 168 nodes investigated.
EXAMPLE 4:
The MCrAIY alloy foil material as described in Example 2 was processed into a cellular body having dimensions of L = 55 mm, B = 35 mm and H = 8 mm, as described above. The cellular structure had the cell dimensions zs given in Example 3 when measured as in Example I. The further, processing of this cellular structure including resistance welding and powder filling and the braze filler metal powder, type and amount were exactly the same as those used in Example 3. The assembly was brazed in the same furnace run as the assembly described in Example 3. The wicking result after brazing, as assessed by the procedure described in Example 1, was 84%. A total of 114 nodes were investigated.
EXAMPLE 5:
The MCrAIY alloy foil material of the composition described in Examples 2 and 4 was processed into a cellular structure body having outside dimensions as before, L = 55 mm, B=35 mm and H = 8 mm. The cellular structure, however, had the special six-sided honeycomb cellshapeinaccoxdancewithttiepresentinvention. Thecellwidth, as measured

as the minimum internal distance w between cell walls forming the double wall crests or nodes was 1.59 mm and the cell dimension b, measured as the minimum distance between the single foil thickness cell walls, was 2.41 mm, giving a ratio of b:w = 1.52 or a ratio of y/ w=2.31. This honeycomb structure was resistance welded to the same backplate material as used in Examples 1 through 4 with the nodal height H being at 90° to the backplate. Braze alloy filler metal, as used in Examples 3 and 4, rilled the cells. This assembly was brazed in the same furnace run as the assemblies described in Examples 3 and 4. The braze wicking result, determined in the manner as described in Example 1, was 95%. A total of 114 nodes were investigated.
EXAMPLE 6:
The MCrAlY alloy foil material having the composition described in Examples 2, 4 and 5 was provided in a cellular structure body form having outside dimensions as before but with the cell shape as described in Example 5, Le. having a ratio of b;w of 1.52. The further processing and additional materials used to provide an assembly for brazing as before were the same as described in Example 5, except the amount of braze filler metal was 9.8 g. This assembly was heated to a temperature of 1190°C and kept at that temperature for 4 minutes. The braze wicking success, determined in the manner as described in Example 1, was 100%. A total of 220 nodes were investigated.
EXAMPLE 7:
The MCrAlY alloy foil material havingthe composition described in Example 3 was provided as a cellular structure body having a nodal height H of 7.5 mm and a honeycomb cell shape according to the present invention with the cell dimension w, as measured as the minimum internal distance between the cell walls forming the double wall crests or nodes of the cell, being 1.45 mm and the cell dimension b, measured as the minimum internal distance between the single wall thickness cell walls, being 2.08 mm, giving a ratio of b:w of 1.43. This cellular structure body was placed standing on edge on a metal backing plate having the nominal chemical composition of 10% by weight Co, 6.6% by weight Cr, 6.5% by weight Ta, 6.4% by weight W, 5.5% by weight AL 3.0% by weight Re, 1.0% by weight TL 0.6% by weight Mo, 0,09% by weight Hf, balance Ni and being provided in a cast,

monocrystalline form. The cellular structure was placed OIL the backing metal by putting a weight on top of the cellular structure which, as before, had the direction ofthe nodal height H at 90° to the baclcplate. Braze alloypowder having the nominal chemical composition of 21% by weight Cr, 4.5% by weight W, 2.4% by weight B, 1.6% by weight Si, 0.1% by weight C, balance Co, was filled into the cells. This assembly was heated to a temperature of 1210°C and held at that temperature for 2 rninutes in a conventional vacuum furnace. This caused the braze filler metal to melt and rise up the double or nodal walls. The braze wicking result, determined as described in Example 1, was 96%.
Table 1 below gives a summary of braze wicking test results for direct comparison, the test samples having in common the same MCrAlY foil materi ak the same braze alloy and the same backing plate material.
TABLE 1
Example No. Cell Shape Braze Wicking Result
4 b:w*l; y:w = l.l6 84%
prior art
5 b:w=1.52; y:w = 2.31 95%
as per present invention
6 b:w=1.52; y:w = 2,31 100%
as per present invention
The ratio m± was measured to be 0.98 to 1.03 for the prior art structure according to Example 4 and the ratio m:k was assessed to be 1.30 to 1.36 for the novel cellular structures according to Examples 5 and 6.
Table 2 below gives a summary of braze wicking results achieved using the same MCrAlY foil material and using similar Co-base braze filler metals in different cell shapes.

TABLE2
Example No. Cell Shaoe Braze WiclrinE Result
3 b:w=l; y:w = 1.18 prior art S%
7 . b:w = 1.43; y:w=2.40 as per present invention 96%
Table 3 gives an overview of all braze tests performed with the same MCrAlY alloy for direct comparison of dififereat braze filler alloys on prior art cell shapes and the cells of the present invention. *

TABLE 3
Example Braze
NP. Cell Shape Braze Allov Braze Cvcle Wicking Result
2a prior art Ni-Cr-Si-C 1193°C/6min 54%
2b prior art Ni-Cr-Si-C H93°C/6min 71%
3 prior art Co-Cr-Ni-Si-W-B-C 1204eC/4min 8%
4 pnorart Co-Cr-Ni-Si-W-B-C 1204°C/4min 84%
5 per present invention Co-Cr-Ni-Si-W-B-C 1204°C/4rain 95%
6 per present invention Co-Cr-Ni-Si-W-B-C 1190°C/4mm 100 %
7 per present invention Co-Cr-W-B-Si-C 1210°C/2min 96%
The above tables and examples demonstrate that good braze wicking, L e. better man 95% when determined as described in Example L, with good reinforcement and consequently good long term dimensional stability of the cellular structures, was achieved with the honeycomb cell shape according to the present invention. This is particularly evident by comparing the results of Example 3 to that of Example 7 and the results of Examples 2 and 4 to those of Examples 5 and 6. 100% braze wicking is achieved with conventional Ni-base alloys when prior art cell shapes are used However, with MQAIY foil materials, braze wicking results of only 8 to 84% were achieved when using this standard cell shape.

All the cellular structures of Examples 5,6 and 7 showed excellent shape stability and oxidation resistance when tested in air at temperatures higher than 850°C, and good resistance against caibunzation attack was observed when exposed to high speed burner gases also at temperatures higher than 350 °C.
MCrAlY foil or sheet material having thick gauges advantageously can be formed into a honeycomb cellular structure according to the present invention as discussed in Examples 8 and 9 below with reference to Figure 4.
EXAMPLE 8:
An MCrAlY alloy having the nominal chemical composition of 16% by weight Cr, 4.5% by weight AJ, 3% by weight Fe, 0.1% maximum by weight Zr, 0.01% by weight Y, 0.7% by weight maviTimiTn Mn + Si, 0.05% by weight C, balance, apart from interstitial impurities, being Ni was provided in the form of thick foil having a thickness of s = 0.254 mm (0.010"). This thick foil material was corrugated and welded to provide a cellular structure having outside dimensions of L = 100 mm, B = 38 mm and H = 10 mm. The cell size characteristics of this cellular structure were: w = 1.48 mm, b = 2.44 mm, hence b/w = 1.67, y - 3.66 mm, m = 1.46 mm and k - 1.07 mm and hence m:k - 1.36. The cellular structure shown in Figure 4 could easily be manufactured in this special cell shape. AH attempts to provide a cellular structure according to the prior art design, i.e. having a ratio of b:w=approx. 1, with values of b = w = 1.0 to 2.0 mm, failed.
EXAMPLE 9:
A conventional, non MCrAlY foil alloy, having the chemical composition of 25% by weight Cr, 10% by weight Mo, 0.05% by weight C and 0.03% by weight Ce was provided in the form of thick foil having a gauge of 0.254 mm (0.010"). This foil material was corrugated and welded to provide a cellular structure body having outside dimensions as in Example 8. The cell shape characteristics were similar to those of Example 8, in particular the ratio b:w was greater than 1.15 and the ratio m:k was greater than 1. This cellular structure was fabricated. Again, all attempts to fabricate conventional hexagonal cell shape structural bodies from the aforementioned foil material failed when cell dimensions w = b = 1.0 to 2.0 mm were envisaged.

segments or cast backing members of a nickel-base alloy forming part of the shroud of the gas turbine of a jet engine or a stationary gas turbine.
The preferred metal foil or sheet alloy of the invention consists of 6 to 30% by
weight Cr, 2 to 7% by weight A], 0.005 to 0.6% by weight Y, at least one of the elements
i selected from the group consisting of Zr, Hf, Ce, La, Si, Mn, Ti in the amount of up to
0.6% by weight and C in the amount of up to 0.3% by weight, at least 6% by weight Fe,
and the balance, apart from impurities, being Fe or Ni or combinations thereof.
The honeycomb cellular structure 30 is attached to backplate 46 by resistance welding or laser spot welding. A braze filler metal in powder form then is applied by filling the vertically aligned cells with the braze powder and the assembly heated to above the melting point of the braze powder, preferably in the range of about 1190°C to 1215°C, in a conventional vacuum furnace for a time sufficient such as about 2 to 8 minutes to melt and wet the nodal walls of the honeycomb cellular structure and to rise up the double nodal walls by capillary action to effectively join the structure to the backplate and to stiffen the honeycomb cellular structure. Suitable cobalt-base braze filler metal alloys for the MCrAlY honeycomb structure can consist of 19% by weight Cr, 17% by weight Ni, 8% by weight Si, 4% by weight W, 0.8% by weight B, 0.4% by weight C and the balance Co, or 21% by weight Cr, 4.5%"by weight W, 2.4% by weight B,1.6% by weight Si, 0.1% by weight C, and the balance Co.
The abradable turbine seal of the invention will now be described with reference to the following non-limitative examples.
EXAMPLE 1:
A conventional, non MCrAlY alloy having the nominal chemical composition of 22% by weight Cr, 18% by weight Fe, 9% by weight Mo, 1.5% by weight Co, 0.6% by weight W, balance Ni was provided in me form of 125 /m (0.125 mm, 0.005") thick foil to form a cellular structure illustrated in Figure I having a length L of 55 mm, a width B of 35 mm and a nodal height H of 8 mm, by corrugating and laser spot welding the foil to form a six-sided honeycomb cell shape having a nodal cell size as measured as the minimum internal distance between the cell walls forming the nodal walls of w = 1.59 mm and a cell size b, measured as the minimum internal distance between opposed single foil thickness

It will be understood, of course, that modifications can be made in the embodiments of the invention illustrated and described herein without departing from the scope and purview of the invention as defined by the appended claims.

WE CLAIM:
1. A honeycomb structure comprising a plurality of abutting semi-hexagonal corrugated metal strips brazed to a metal backplate, each corrugated metal strip having alternating flat slanted sides interconnected by a flat crest, the abutting strips joined together at adjacent flat crests by welding to form generally hexagonal cells, the slanted sides having an equal length and the crests having a length greater than the slanted sides whereby the cell width w measured between opposed flat crests of adjacent strips relative to the distance b between the planes of opposed slanted sides has a ratio of b:w of greater than 1.15:1.0.
2. A honeycomb structure as claimed in claim 1, wherein the ratio of b:w is 1.2 to 2.0:1.0.
3. A honeycomb structure as claimed in claim 1, wherein the ratio of b:w is 1.3 to 1.6:1.0.
4 A honeycomb structure as claimed in claim 1, wherein the semi-hexagonal corrugated strips are a foil metal or sheet metal alloy consisting of 6 to 30% by weight Cr, 2 to 7% by weight Al, 0.005 to 0.6% by weight Y, up to 0.6% by weight of at least one of the elements selected from the group consisting of Zr, Hf, Ce, La, Si, Mn and Ti, 0 to 0.3% by weight C, at least 6% by weight Fe, and the balance, apart from impurities, being Fe or Ni or combinations thereof.
5. An abradable seal for use in a gas turbine comprising a metal backplate and a honeycomb structure attached standing on edge to the metal backplate comprising a metal foil or sheet metal wherein the metal foil or sheet metal consisting of 6 to 30% by weight Cr, 2 to 7% by weight Al, 0.005 to 0.6% by weight Y, up to 0.6% by weight of at least one of the elements selected from the group consisting of Zr, Hf, Ce, La, Si, Mn and Ti, 0 to 0.3% by weight C, at least 6% by weight Fe, and the balance, apart from impurities, being Fe or Ni or combinations thereof.

6. An abradable seal as claimed in claim 5, wherein the metal backplate is a nickel-base alloy in the form of a metal backing sheet ring, sheet metal ring segments or cast backing member and the metal foil or sheet metal used to manufacture the honeycomb has a thickness of 0.100 mm to 0.400 mm.
7. An abradable seal as claimed in claim 6 wherein the honeycomb structure comprises a plurality of abutting semi-hexagonal corrugated metal foil or sheet metal strip each having alternating flat slanted sides interconnected by a flat crest, the abutting strips joined together at adjacent flat crests by welding to form generally hexagonal cells, the slanted sides having an equal length and the crests having a length greater than the slanted sides whereby the cell width w measured between opposed flat crests of adjacent strips relative to the distance b between the planes of opposed slanted sides has a ratio of b:w of greater than 1.15:1.0.
8. An abradable seal as claimed in claim 7, wherein the ratio of b:w is 1.2 to 2.0:1.0.
9. An abradable seal as claimed in claim 7, wherein the ratio of b:w is 1.3 to 1.6:1.0.
10. An abradable seal as claimed in claim 7, in which the honeycomb structure is attached to the metal backplate by brazing.
11. A method of forming an abradable seal for use in a gas turbine comprising forming a plurality of corrugated strips of a foil metal or sheet metal alloy consisting of 6 to 30% by weight Cr, 2 to 7% by weight Al, 0.005 to 0.6% by weight Y, up to 0.6% by weight of at least one of the elements selected from the group consisting of Zr, hf, Ce, La, Si, Mn and Ti, 0 to 0.3% by weight C, at least 6% by weight Fe, and the balance, apart from impurities, being Fe or Ni or combinations thereof, said strips each having alternating flat slanted sides interconnected by a flat crest, abutting the strips together at adjacent flat crests, welding the strips together at the adjacent flat crests to form generally hexagonal cells, the slanted sides having an equal length and the crests having a length greater than the slanted sides whereby the cell

width w measured between opposed flat crests of adjacent strips relative to the distance b between the planes of opposed slanted sides has a ratio of b:w of greater than 1.15:1.0, and brazing the hexagonal structure standing on edge to a nickel-base backplate.
12. A method as claimed in claim 11, wherein the ratio of b:w is 1.2 to 2.0:1.0.
13. A method as claimed in claim 11, wherein the ratio of b:w is 1.3 to 1.6:1.0.
Dated this May 20, 2003.
(RICHA PANDEY)
OF REMFRY AND SAGAR ATTORNEY FOR THE APPLICANTS

Documents:

521-mumnp-2003-assignment(29-12-2006).pdf

521-mumnp-2003-claims(granted)-(02-11-2006).doc

521-mumnp-2003-claims(granted)-(02-11-2006).pdf

521-MUMNP-2003-CORRESPONDENCE(26-3-2010).pdf

521-mumnp-2003-correspondence(29-12-2006).pdf

521-mumnp-2003-correspondence(ipo)-(19-04-2007).pdf

521-mumnp-2003-drawing(02-11-2006).pdf

521-mumnp-2003-form 13(12-04-2006).pdf

521-mumnp-2003-form 18(25-11-2005).pdf

521-mumnp-2003-form 1a(20-05-2003).pdf

521-mumnp-2003-form 1a(21-08-2003).pdf

521-mumnp-2003-form 2(granted)-(02-11-2006).doc

521-mumnp-2003-form 2(granted)-(02-11-2006).pdf

521-MUMNP-2003-FORM 26(26-3-2010).pdf

521-mumnp-2003-form 3(10-08-2006).pdf

521-mumnp-2003-form 3(12-04-2006).pdf

521-mumnp-2003-form 3(20-05-2003).pdf

521-mumnp-2003-form 5(12-04-2006).pdf

521-mumnp-2003-form 6(25-08-2003).pdf

521-mumnp-2003-form-pct-ipea-409(20-05-2003).pdf

521-mumnp-2003-form-pct-isa-210(20-05-2003).pdf

521-mumnp-2003-power of authority(09-09-2003).pdf

521-mumnp-2003-power of authority(12-04-2006).pdf

521-mumnp-2003-power of authority(20-05-2003).pdf

abstract1.jpg


Patent Number 206205
Indian Patent Application Number 521/MUMNP/2003
PG Journal Number 28/2007
Publication Date 13-Jul-2007
Grant Date 19-Apr-2007
Date of Filing 20-May-2003
Name of Patentee THE WESTAIM CORPORATION
Applicant Address 10102-114 STREET, FORT SASKATCHEWAN, ALBERTA, CANADA T8L 3W4.
Inventors:
# Inventor's Name Inventor's Address
1 RICHARD CHARLES HAMMERSLEY 30 CHADKIRK ROAD, ROMILEY, STOCKPORT SK6 7HJ, ENGLAND.
2 DIETER RUDOLF SPORER HIRNBEINSTRASSE 2, D-87527 SONTHOFEN, GERMANY.
PCT International Classification Number B23K 11/00
PCT International Application Number PCT/CA01/01676
PCT International Filing date 2001-11-26
PCT Conventions:
# PCT Application Number Date of Convention Priority Country
1 09 / 722,060 2000-11-27 U.S.A.