Combustion chamber

Patent metadata

Field	Value
Publication number	US-10655857-B2
Application number	US-201715637209-A
Country	US
Kind code	B2
Filing date	Jun 29, 2017
Priority date	Jul 29, 2016
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

A gas turbine engine combustion chamber includes upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. The upstream end of each combustion chamber segment includes a surface having a plurality of circumferentially spaced radially extending holes and the upstream ring structure having a plurality of circumferentially spaced holes extending radially through a portion abutting the surface of the upstream end of each combustion chamber segment. Each combustion chamber segment being removably secured to the upstream ring structure by a plurality of fasteners locatable in the holes in the combustion chamber segment and corresponding holes in the upstream ring structure.

First claim

The invention claimed is:

1. A combustion chamber comprising:
a downstream ring structure;
a plurality of circumferentially-arranged combustion chamber segments, each combustion chamber segment of the plurality of combustion chamber segments extending a full length of the combustion chamber, each combustion chamber segment including a frame structure integral with an inner wall;
an upstream ring structure having a portion abutting a surface of an upstream end of each combustion chamber segment of the plurality of combustion chamber segments, the upstream end of each combustion chamber segment of the plurality of combustion chamber segments being secured to the upstream ring structure and having a plurality of circumferentially-spaced radially-extending chamber holes, and a downstream end of each combustion chamber segment is mounted on the downstream ring structure;
a plurality of circumferentially-spaced ring holes extending radially through the portion of the upstream ring structure and each combustion chamber segment of the plurality of combustion chamber segments being removably secured to the upstream ring structure by a plurality of fasteners disposed in the plurality of chamber holes and corresponding ring holes; and
a cowl having a downstream end including a plurality of circumferentially-spaced flaps, each flap of the plurality of flaps being located at an interface between two adjacent combustion chamber segments of the plurality of combustion chamber segments,
wherein the plurality of chamber holes includes:
a first chamber hole corresponding with a first ring hole of the plurality of ring holes to circumferentially position a corresponding combustion chamber segment relative to the upstream ring structure, and
a second chamber hole corresponding with a second ring hole of the plurality of ring holes to allow relative circumferential thermal expansion between the combustion chamber segment and the upstream ring structure, and either (i) the second chamber hole is wider than the first chamber hole in a circumferential direction of the combustion chamber, or (ii) the second ring hole is wider than the first ring hole in the circumferential direction of the combustion chamber, such that a gap is formed between a corresponding fastener of the plurality of fasteners and sides of the second chamber hole or sides of the second ring hole when the corresponding fastener fastens the corresponding combustion chamber segment to the upstream ring via the second chamber hole and the second ring hole, and

wherein the plurality of fasteners include at least one bolt securing two adjacent combustion chamber segments of the plurality of combustion chamber segments to the upstream ring structure, the at least one bolt being disposed under a respective flap of the plurality of flaps such that a head of the at least one bolt is covered by the respective flap of the plurality of flaps.

2. The combustion chamber as claimed in claim 1 , wherein the plurality of ring holes includes a plurality of first ring holes and a plurality of second ring holes, the plurality of first ring holes and the plurality of second ring holes being arranged circumferentially and alternately around the upstream ring structure, each second ring hole being circumferentially slotted, each first ring hole being aligned axially and circumferentially with a corresponding first chamber hole of the plurality of chamber holes and each second ring hole being aligned axially with a corresponding second chamber hole of the plurality of chamber holes to allow relative circumferential thermal expansion between the combustion chamber segment and the upstream ring structure, each first ring hole of the plurality of first ring holes having a same diameter as a diameter of the first chamber hole of the plurality of chamber holes.

3. The combustion chamber as claimed in claim 1 , wherein the first and second chamber holes of the plurality of chamber holes are arranged circumferentially alternately, each first chamber hole has a same diameter as a diameter of the plurality of ring holes, each second chamber hole is circumferentially slotted, each first chamber hole is aligned axially and circumferentially with a corresponding ring hole of the plurality of ring holes, and each second chamber hole is aligned axially with a corresponding ring hole of the plurality of ring holes to allow relative circumferential thermal expansion between the combustion chamber segment and the upstream ring structure.

4. The combustion chamber as claimed in claim 1 , wherein the plurality of fasteners include nuts and bolts.

5. The combustion chamber as claimed in claim 1 , wherein the combustion chamber is selected from a group consisting of an annular combustion chamber and a tubular combustion chamber.

6. The combustion chamber as claimed in claim 5 , wherein the combustion chamber segments form a radially outer annular wall of the annular combustion chamber.

7. The combustion chamber as claimed in claim 6 , wherein the combustion chamber segments form a radially inner annular wall of the annular combustion chamber.

8. The combustion chamber as claimed in claim 1 , wherein the combustion chamber is in a gas turbine engine.

9. The combustion chamber as claimed in claim 8 , wherein the gas turbine engine is an aero gas turbine engine, a marine gas turbine engine, an industrial gas turbine engine, or an automotive gas turbine engine.

10. The combustion chamber as claimed in claim 9 , wherein the aero gas turbine engine is a turbofan gas turbine engine, a turbojet gas turbine engine, a turbo propeller gas turbine engine, or a turbo shaft gas turbine engine.

11. The combustion chamber as claimed in claim 1 , wherein at least some chamber holes of the plurality of chamber holes extending radially through the upstream end of each combustion chamber segment are axially slotted.

12. The combustion chamber as claimed in claim 1 , wherein the cowl is secured to the upstream ring structure, the cowl including a plurality of circumferentially-spaced radially-extending cowl holes, the cowl being removably secured to the upstream ring structure by a plurality of fasteners disposed in the plurality of cowl holes corresponding to the plurality of chamber holes in the combustion chamber segments and the plurality of ring holes in the upstream ring structure.

13. The combustion chamber as claimed in claim 12 , wherein:
the corresponding chamber holes of the plurality of chamber holes are cylindrical and have a larger diameter than the corresponding ring holes of the plurality of ring holes,
a first plurality of cowl holes are cylindrical and have a same diameter as the diameter of the corresponding ring holes of the plurality of ring holes, and
a second plurality of cowl holes are circumferentially slotted.

14. The combustion chamber as claimed in claim 1 , wherein:
each combustion chamber segment includes a box structure, the box structure including:
the frame structure,
the inner wall, and
an outer wall, and

the frame structure, the inner wall, and the outer wall are integral.

15. The combustion chamber as claimed in claim 1 , wherein each combustion chamber segment includes a first edge and a second edge spaced circumferentially from the first edge, the first edge of each combustion chamber segment of the plurality of combustion chamber segments having a first hook arranged at a first radial distance, the second edge of each combustion chamber segment of the plurality of combustion chamber segments having a second hook arranged at a second radial distance, the second radial distance being greater

Assignees

• Rolls Royce Plc

Inventors

• Harding Stephen C
• Hucker Paul A

Classifications

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F23R3/44

  Combustion chambers comprising a {single} tubular flame tube within a tubular casing (reverse-flow combustion chambers F23R3/54) · CPC title

• F23R3/20 Primary

  incorporating fuel injection means · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title