Sectioned engine structure for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11732610-B2
Application number	US-202117535078-A
Country	US
Kind code	B2
Filing date	Nov 24, 2021
Priority date	Nov 24, 2021
Publication date	Aug 22, 2023
Grant date	Aug 22, 2023

Abstract

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

First claim

What is claimed is:

1. An assembly for a gas turbine engine, comprising:
a stationary engine structure including a diffuser, a combustor, an engine case and a plenum, the combustor disposed within the plenum, the engine case forming a peripheral boundary of the plenum, and a gas path extending sequentially through the diffuser, the plenum and the combustor;
a first section of the stationary engine structure formed as a first monolithic body, the first section including the diffuser and the combustor; and
a second section of the stationary structure formed as a second monolithic body, the second section comprising the engine case;
wherein the second section circumscribes the first section.

2. The assembly of claim 1 , wherein
the diffuser includes a first wall, a second wall and a plurality of vanes; and
each of the plurality of vanes is within the gas path and extends between the first wall and the second wall.

3. The assembly of claim 1 , wherein the combustor is configured as a reverse-flow combustor.

4. The assembly of claim 1 , wherein
the stationary engine structure further includes a turbine nozzle downstream of the combustor along the gas path; and
the first section further includes the turbine nozzle.

5. The assembly of claim 4 , wherein the diffuser and the turbine nozzle share a common wall.

6. The assembly of claim 4 , wherein
the turbine nozzle includes a first wall, a second wall and a plurality of vanes; and
each of the plurality of vanes is within the gas path and extends between the first wall and the second wall.

7. The assembly of claim 1 , further comprising:
a turbine rotor;
the stationary engine structure further including a turbine case housing the turbine rotor and forming a peripheral boundary of the gas path; and
the first section further including the turbine case.

8. The assembly of claim 1 , wherein
the stationary engine structure further includes an exhaust duct forming a peripheral boundary of the gas path; and
the first section further including the exhaust duct.

9. The assembly of claim 1 , wherein the second section is bonded to the first section through a butt joint.

10. The assembly of claim 1 , wherein the second section is bonded to the first section through a splice joint.

11. The assembly of claim 1 , wherein
the engine case extends axially along and circumferentially about an axis, and the engine case includes a side wall and an end wall;
the side wall projects axially out from the end wall to an axial end of the engine case, and the engine case is attached to the first section at the axial end; and
the end wall projects radially in from the side wall to a radial end of the engine case, and the engine case is attached to the first section at the radial end.

12. An assembly for a gas turbine engine, comprising:
a stationary engine structure including a diffuser, a combustor, an engine case and a plenum, the combustor disposed within the plenum, the engine case forming a peripheral boundary of the plenum, and a gas path extending sequentially through the diffuser, the plenum and the combustor;
a first section of the stationary engine structure formed as a first monolithic body, the first section including the diffuser and the combustor; and
a second section of the stationary structure formed as a second monolithic body, the second section comprising the engine case;
wherein the stationary engine structure further includes a fuel conduit and a nozzle;
wherein the nozzle is configured to receive fuel from the fuel conduit and inject the fuel into a volume of the combustor; and
wherein the second section further includes at least one of the fuel conduit or the nozzle.

13. The assembly of claim 12 , wherein
the stationary structure further includes a fuel manifold outside of the engine case;
the fuel manifold is configured to supply the fuel to the fuel conduit; and
the second section further includes the fuel manifold.

14. The assembly of claim 12 , wherein at least a portion of the fuel conduit projects out from the engine case into the plenum towards the fuel injector.

15. An assembly for a gas turbine engine, comprising:
a stationary engine structure including a diffuser, a combustor, an engine case and a plenum, the combustor disposed within the plenum, the engine case forming a peripheral boundary of the plenum, and a gas path extending sequentially through the diffuser, the plenum and the combustor;
a first section of the stationary engine structure formed as a first monolithic body, the first section including the diffuser and the combustor; and
a second section of the stationary structure formed as a second monolithic body, the second section comprising the engine case;
wherein the stationary engine structure further includes an inlet section and a compressor case;
wherein the compressor case forms a peripheral boundary of the gas path between the inlet section and the diffuser; and
wherein a third section of the stationary structure includes the inlet section and the compressor case, and the third section is attached to the first section.

16. An assembly for a gas turbine engine, comprising:
a diffuser including an inner diffuser wall and an outer diffuser wall;
a combustor including an inner combustor wall, an outer combustor wall and a bulkhead extending between and connected to the inner combustor wall and the outer combustor wall;
a duct wall;
an engine wall including a side wall and an end wall, the side wall projecting out from the end wall to the outer diffuser wall, the side wall brazed to the outer diffuser wall, the end wall projecting out from the side wall to the duct wall, and the end wall brazed to the duct wall; and
a monolithic body including the diffuser, the combustor and the duct wall.

Assignees

• Raytheon Tech Corp

Inventors

• Binek Lawrence A
• Jackson Sean R

Classifications

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• F23R3/002 Primary

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

• F05D2220/32

  in gas turbines · CPC title