1 A method of manufacturing a hollow component for a gas turbine engine, in which method a coating of a damping material is provided on an internal surface of the component.
2 A method as claimed in claim 1, in which the component is manufactured from a plurality of panels which are joined together to form the hollow component, the damping material being applied to at least one of the panels before the panels are joined together.
3 A method as claimed in claim 2, in which the panels are joined together in a diffusion bonding process.
4 A method as claimed in claim 3, in which the component comprises two of the said panels, the method comprising:
(a) joining the panels together at adjacent edge regions in the diffusion bonding process;
(b) deforming the panels by applying internal pressure between the panels, thereby to create an internal cavity.
5 A method as claimed in claim 4, in which step (b) comprises heating the panels and deforming them superplastically.
6 A method as claimed in claim 4, in which an intermediate membrane is disposed between the panels, the membrane being bonded in the diffusion bonding process to each of the panels at spaced locations, the damping material being situated outside the spaced locations, whereby deformation of the panels under the internal pressure causes the membrane to form partitions extending between the panels across the internal cavity.
7 A method as claimed in claim 6, in which a stop-off material is applied to the damping coating to prevent or minimise diffusion bonding between the membrane and the damping coating.
8 A method as claimed in claim 7, in which the stop-off material comprises yttria.
9 A method as claimed in claim 6, in which the damping material is applied to the panels in a striped pattern, the spaces between adjacent stripes on one of the panels being disposed opposite a stripe on the other panel, whereby the membrane forms a warren girder structure within the component.
10 A method as claimed in claim 1, in which the damping material is applied within a recess in a substrate of the component.
11 A method as claimed in claim 10, in which the damping material is applied within the recess to form a damping material surface which lies below the surrounding surface of the substrate.
12 A method as claimed in claim 1, in which the damping material is applied by a plasma spraying process.
13 A method as claimed in claim 1, in which the component is a fan blade of a gas turbine engine.
14 A process for manufacturing a blisk, the process comprising manufacturing a plurality of fan blades, by a method in accordance with claim 1, and subsequently welding the fan blades to a disc.
15 A hollow component for a gas turbine engine of which an internal surface is provided with a coating of a damping material.
16 A hollow component as claimed in claim 15, in which the damping material is a ceramic material.
17 A hollow component as claimed in claim 16, in which the damping material is a spinel.
18 A hollow component as claimed in claim 17, in which the damping material is magnesia alumina spinel.
19 A hollow component as claimed in claim 15, in which the damping material is situated in a recess in a substrate of the component.
20 A hollow component as claimed in claim 19, in which the surface of the damping material lies beneath the surrounding surface of the substrate material.
21 A hollow component as claimed in claim 15, in which the component comprises an outer wall defining the interior of the component, a partition structure being disposed within the interior of the component, and contacting the outer wall at spaced contact regions, the damping material being applied to the internal surface of the outer wall at regions between the contact regions.
22 A hollow component as claimed in claim 21, in which the partition structure comprises a warren girder structure, the contact regions comprising parallel, elongate regions.
23 A hollow component as claimed in claim 21, in which the outer wall comprises two panels which are bonded together at opposite edges.
24 A hollow component as claimed in claim 15, in which the damping material is applied to a substrate of titanium alloy.
25 A hollow component as claimed in claim 15, which comprises a fan blade.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
What is claimed is:
1. An isolated polynucleotide comprising a member selected from the group consisting of:
(a) a polynucleotide encoding a polypeptide having the deduced amino acid sequence of SEQ ID NO:2 or a fragment of said polypeptide;
(b) a polynucleotide encoding a polypeptide having the amino acid sequence encoded by the cDNA contained in ATCC Deposit No. 75649;
(c) a polynucleotide encoding a polypeptide having the deduced amino acid sequence of SEQ ID NO:4 or a fragment of said polypeptide;
(d) a polynucleotide encoding a polypeptide having the amino acid sequence encoded by the cDNA contained in ATCC Deposit No. 75651;
(e) a polynucleotide encoding a polypeptide having the deduced amino acid sequence of SEQ ID NO:6 or a fragment of said polypeptide; and
(f) a polynucleotide encoding a polypeptide having the amino acid sequence encoded by the cDNA contained in ATCC Deposit No. 75650.
2. The polynucleotide of claim 1 wherein the polynucleotide is DNA.
3. The polynucleotide of claim 1 wherein said polynucleotide encodes a polypeptide having the deduced amino acid sequence of SEQ ID NO:2.
4. The polynucleotide of claim 1 wherein said polynucleotide encodes a polypeptide having the deduced amino acid sequence of SEQ ID NO:4.
5. The polynucleotide of claim 1 wherein said polynucleotide encodes a polypeptide having the deduced amino acid sequence of SEQ ID NO:6.
6. The polynucleotide of claim 1 wherein said polynucleotide encodes a polypeptide encoded by the cDNA of ATCC Deposit No. 75649.
7. The polynucleotide of claim 1 wherein said polynucleotide encodes a polypeptide encoded by the cDNA of ATCC Deposit No. 75651.
8. The polynucleotide of claim 1 wherein said polynucleotide encodes a polypeptide encoded by the cDNA of ATCC Deposit No. 75650.
9. A vector containing the polynucleotide of claim 1.
10. A host cell genetically engineered with the vector of claim 9.
11. A process for producing a polypeptide comprising expressing from the host cell of claim 10 the polypeptide encoded by said DNA.
12. A process for producing cells capable of expressing a polypeptide comprising genetically engineering cells with the vector of claim 9.
13. A polypeptide comprising a member selected from the group consisting of:
(a) a polypeptide having the deduced amino acid sequence of SEQ ID NO:2 and fragments thereof;
(b) a polypeptide encoded by the cDNA of ATCC Deposit No. 75649 and fragments of said polypeptide;
(c) a polypeptide having the deduced amino acid sequence of SEQ ID NO:4 and fragments thereof;
(d) a polypeptide encoded by the cDNA of ATCC Deposit No. 75651 and fragments of said polypeptide;
(e) a polypeptide having the deduced amino acid sequence of SEQ ID NO:6 and fragments thereof; and
(f) a polypeptide encoded by the cDNA of ATCC Deposit No. 75650 and fragments of said polypeptide.
14. An antibody that specifically binds the polypeptide of claim 13.