Combustion chamber heat shield and seal assembly and a method of manufacturing a combustion chamber heat shield and seal assembly

Patent metadata

Field	Value
Publication number	US-9562474-B2
Application number	US-201414173146-A
Country	US
Kind code	B2
Filing date	Feb 5, 2014
Priority date	Mar 8, 2013
Publication date	Feb 7, 2017
Grant date	Feb 7, 2017

Abstract

A gas turbine engine combustion chamber heat shield and seal assembly comprises a heat shield and a seal. The heat shield has an aperture and the seal is located in the aperture in the heat shield. The seal comprises an annular member having an upstream end, a middle and a downstream end. The upstream end of the seal has a diameter greater than the diameter of the aperture in the heat shield, the middle has a diameter less than the diameter of the aperture in the heat shield and the downstream end of the seal has a diameter greater than the diameter of the aperture in the heat shield.

First claim

The invention claimed is:

1. A combustion chamber heat shield and seal assembly comprising a heat shield and a seal,
the heat shield having an aperture, and
the seal being located in the aperture in the heat shield,
the seal comprising an annular member having an upstream end, a middle and a downstream end, the upstream end of the seal having an outer diameter greater than the diameter of the aperture in the heat shield, the middle having a diameter less than the diameter of the aperture in the heat shield and the downstream end of the seal having a diameter greater than the diameter of the aperture in the heat shield.

2. An assembly as claimed in claim 1 wherein the downstream end of the seal is frusto-conical.

3. An assembly as claimed in claim 1 wherein the upstream end of the seal comprises a radially outwardly extending flange.

4. An assembly as claimed in claim 1 wherein the middle of the seal has a plurality of apertures extending there-through.

5. An assembly as claimed in claim 4 wherein the apertures in the middle of the seal are angled in a downstream direction from an inner surface of the seal to an outer surface of the seal.

6. An assembly as claimed in claim 1 wherein the heat shield has a ring defining the aperture and the ring has a plurality of apertures extending there-through.

7. An assembly as claimed in claim 6 wherein the apertures in the ring are angled in a downstream direction from an outer surface of the ring to an inner surface of the ring.

8. An assembly as claimed in claim 1 wherein the heat shield and the seal consist of a superalloy, and the superalloy is selected from the group consisting of a nickel base superalloy, a cobalt base superalloy and an iron base superalloy.

9. A combustion chamber comprising a combustion chamber heat shield and seal assembly as claimed in claim 1 , wherein the combustion chamber having an upstream end wall structure,
the upstream end wall structure comprising an upstream end wall and the heat shield,
the heat shield being spaced from and being arranged downstream of the upstream end wall, the upstream end wall having an aperture and the aperture in the heat shield being aligned with the aperture in the upstream end wall, and
a fuel injector being arranged to locate in the seal positioned in the aperture in the heat shield.

10. A method of making a combustion chamber heat shield and seal assembly, the combustion chamber heat shield and seal assembly comprising a heat shield and a seal, the heat shield having an aperture and the seal being located in the aperture in the heat shield, the seal comprising an annular member having an upstream end, a middle and a downstream end, the upstream end of the seal having an outer diameter greater than the diameter of the aperture in the heat shield, the middle having a diameter less than the diameter of the aperture in the heat shield and the downstream end of the seal having a diameter greater than the diameter of the aperture in the heat shield, the method comprising the steps of:
a) providing a mould, the mould having a first cavity portion having a shape defining the heat shield and a second cavity portion having a shape defining the seal and a third portion interconnecting the first cavity portion and the second cavity portion,
b) supplying metal into the mould such that the first cavity portion, the second cavity portion and the third portion are filled with metal,
c) solidifying the metal in the mould,
d) removing the mould from the metal, and
e) separating the first cavity portion from the second cavity portion of the metal to produce the combustion chamber heat shield and seal assembly.

11. A method as claimed in claim 10 wherein step b) comprises casting molten metal into the mould such that the first cavity portion, the second cavity portion and the third portion are filled with molten metal, step c) comprises solidifying the molten metal in the mould to form a metal casting, step d) comprises removing the mould from the metal casting, and step e) comprises separating the first cavity portion from the second cavity portion of the metal casting to produce the combustion chamber heat shield and seal assembly.

12. A method as claimed in claim 10 wherein step b) comprises providing a composition comprising a mixture of metal powder and a binder, metal injection moulding the composition into the mould such that the first cavity portion, the second cavity portion and the third portion are filled with the composition, step c) comprises solidifying the composition in the mould to form a green compact, step d) comprises removing the mould from the green compact, removing binder from the green compact to form a brown compact and sintering the brown compact to remove the remainder of the binder and to fuse the metal powder together to form a metal injection moulding, and step e) comprises separating the first cavity portion from the second cavity portion of the metal injection moulding to produce the combustion chamber heat shield and seal assembly.

13. A method as claimed in claim 10 wherein the first cavity portion is separated from the second cavity portion by machining.

14. A method as claimed in claim 13 wherein the first cavity portion is separated from the second cavity portion by turning.

15. A method as claimed in claim 10 wherein the first cavity portion is separated from the second cavity portion by machining through the third portion.

16. A method as claimed in claim 10 wherein the upstream end or the downstream end of the seal is separated from the heat shield by machining.

17. A method as claimed in claim 16 wherein the upstream end or the downstream end of the seal is separated from the heat shield by turning.

18. A method as claimed in claim 10 wherein the upstream end or the downstream end of the seal and the heat shield is arranged coaxially in the mould.

19. A method as claimed in claim 10 wherein the heat shield and the seal are formed from a superalloy, and the superalloy is selected from the group consisting of a nickel base superalloy, a cobalt base superalloy and an iron base superalloy.

20. A method of making a combustion chamber heat shield and seal assembly, the combustion chamber heat shield and seal assembly comprising a heat shield and a seal, the heat shield having an aperture and the seal being located in the aperture in the heat shield, the seal comprising an annular member having an upstream end, a middle and a downstream end, the upstream end of the seal having an outer diameter greater than the diameter of the aperture in the heat shield, the middle having a diameter less than the diameter of the aperture in the heat shield and the downstream end of the seal having a diameter greater than the diameter of the aperture in the heat shield, the method comprising the steps of:
a) providing a powder bed direct radiation deposition apparatus,
b) directing radiation in a predetermined pattern over metal powder in the powder bed direct radiation deposition apparatus to fuse the metal powder to form the seal and to form the heat shield at the same time, and
c) removing the combustion chamber heat shield and the seal assembly from the powder bed direct radiation deposition apparatus.

21. A method as claimed in claim 20 wherein the powder bed direct radiation deposition apparatus directs a laser beam, an electron beam or microwave beam onto the metal powder.

22. A method as claimed in claim 20 wherein the heat shield and the seal are

Assignees

• Rolls Royce Plc

Inventors

• Garry Ian Murray

Classifications

• F02C7/12 Primary

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• B22F10/32

  of the atmosphere, e.g. composition or pressure in a building chamber · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• F02C7/24 Primary

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title