Exhaust nozzle with vane support structure for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11274630-B2
Application number	US-202016803535-A
Country	US
Kind code	B2
Filing date	Feb 27, 2020
Priority date	Feb 27, 2020
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

First claim

What is claimed is:

1. A gas turbine engine comprising
an engine core including a compressor configured to receive and compress an airflow, a combustor configured to receive a compressed airflow from the compressor and combust the compressed airflow to produce hot, high-pressure combustion products, and a turbine configured to interact with the high-pressure combustion products, and
an exhaust nozzle configured to receive the high-pressure combustion products from the engine core and discharge the high-pressure combustion products to the atmosphere, the exhaust nozzle including an outer shroud arranged circumferentially about an axis to define an outer boundary surface of an exhaust nozzle flow path and a nozzle-plug assembly arranged in the exhaust nozzle flow path,
wherein the nozzle-plug assembly includes an inner plug arranged circumferentially about the axis to define an inner boundary surface of the exhaust nozzle flow path, at least one support vane that extends between the outer shroud and the inner plug through the exhaust nozzle flow path, and an expansion-permissive link that interconnects the inner plug to the support vane to support the inner plug in the exhaust nozzle flow path while allowing thermal expansion and contraction of the inner plug and the support vane relative to one another,
wherein the support vane includes a vane-support frame that interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path and an outer vane shell coupled to the vane-support frame to provide an outer flow path boundary for the at least one support vane, and
wherein the vane-support frame includes a plurality of support beams and an endplate coupled to the plurality of support beams and wherein the inner plug includes a plug support frame that is spaced apart from the endplate by a first distance when the exhaust nozzle is in a cold-build state and is spaced apart from the endplate by a second distance, less than the first distance, when the exhaust nozzle is in a hot-use state.

2. The gas turbine engine of claim 1 , wherein the expansion-permissive link includes a load shaft that extends through apertures formed in both the endplate and the plug-support frame, a first bearing sleeve positioned between the load shaft and the endplate of the vane-support structure, and a second bearing sleeve positioned between the load shaft and the plug-support frame.

3. The gas turbine engine of claim 2 , wherein the load shaft is configured to translate relative to the first and second bearing sleeves as the exhaust nozzle changes between the cold-build state and the hot-use state.

4. The gas turbine engine of claim 1 , wherein the inner plug further includes an outer plug shell that defines a vane-receiving space and receives a portion of the outer vane shell therein.

5. The gas turbine engine of claim 4 , wherein the outer vane shell translates relative to the outer plug shell as the exhaust nozzle changes between the cold-build state and a hot-use state.

6. An exhaust nozzle for a gas turbine engine, the exhaust nozzle comprising
an outer shroud arranged circumferentially about an axis to define an outer boundary surface of an exhaust nozzle flow path,
a nozzle-plug assembly including an inner plug arranged circumferentially about the axis to define an inner boundary surface of the exhaust nozzle flow path and a support vane that extends between the outer shroud and the inner plug through the exhaust nozzle flow path, the inner plug including a plug support frame and an outer vane shell, and the support vane including a vane support frame and an outer vane shell, and
an expansion-permissive link that interconnects the plug support frame and the vane support frame to transfer loads from the inner plug, through the support vane, and to the outer shroud,
wherein the expansion-permissive link is configured to allow movement of the support vane relative to the plug support frame between a cold-build state position, in which the vane support frame is spaced apart from the plug support frame by a first distance, and a hot-use state position, in which the vane support frame is spaced apart from the plug support frame by a second distance less than the first distance, and
wherein the vane-support frame includes a plurality of support beams and an endplate coupled to the plurality of support beams, and the expansion-permissive link interconnects the plug support frame to the plurality of support beams and the endplate of the vane-support frame.

7. The exhaust nozzle of claim 6 , wherein the expansion-permissive link includes a load shaft that extends through apertures formed in both the endplate and the plug-support frame, a first bearing sleeve positioned between the load shaft and the endplate of the vane-support structure, and a second bearing sleeve positioned between the load shaft and the plug-support frame.

8. The exhaust nozzle of claim 7 , wherein the load shaft is configured to translate relative to the first and second bearing sleeves as the exhaust nozzle changes between the cold-build state and a hot-use state.

9. The exhaust nozzle of claim 7 , wherein the outer plug shell defines a vane-receiving space and receives a portion of the outer vane shell therein and the outer vane shell translates relative to the outer plug shell as the exhaust nozzle changes between the cold-build state and a hot-use state.

10. The exhaust nozzle of claim 6 , wherein the nozzle-plug assembly includes a first support vane and a second support vane that each interconnect the inner plug and the outer shroud and the expansion-permissive link includes a first support rod coupled to the first support vane and a second support rod coupled to the second support vane.

11. The exhaust nozzle of claim 10 , wherein the first support rod and the second support rod are coupled together and extend axially forward and radially away from the axis to provide a v-shaped expansion-permissive link that allows thermal growth of the first and second vanes in axial and radial directions relative to the axis.

12. The exhaust nozzle of claim 6 , wherein the plurality of support beams include a first set of support beams that extend forward from the inner plug at an acute angle relative to the axis and a second set of support beams that extend transversely to the first set of support beams.

13. The exhaust nozzle of claim 12 , wherein each of the support beams of the second set interconnect at least two of the support beams of the first set.

14. The exhaust nozzle of claim 13 , wherein each of the support beams of the second set extend perpendicularly to each of the support beams of the first set.

15. A gas turbine engine comprising
an engine core including a compressor configured to receive and compress an airflow, a combustor configured to receive a compressed airflow from the compressor and combust the compressed airflow to produce hot, high-pressure combustion products, and a turbine configured to interact with the high-pressure combustion products, and
an exhaust nozzle configured to receive the high-pressure combustion products from the engine core and discharge the high-pressure combustion products to the atmosphere, the exhaust nozzle including an outer shroud arranged circumferentially about an axis to define an outer boundary surface of an exhaust nozzle flow path and a nozzle-plug assembly arranged in the exhaust nozzle flow path,
wherein the nozzle-plug assembly includes an inner plug arranged circumferentially about the axis to define an inner boundary surface of the exhaust nozzle flow path, at least one support vane th

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Sutterfield David L
• Petty Jack D
• Lerg Bryan H
• Sanderson Andrew

Classifications

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title

• F05D2250/34

  translated · CPC title

• F02K1/04 Primary

  Mounting of an exhaust cone in the jet pipe · CPC title

• F02K1/52

  Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title