System for rotor assembly thermal gradient reduction

Patent metadata

Field	Value
Publication number	US-11525400-B2
Application number	US-202016923198-A
Country	US
Kind code	B2
Filing date	Jul 8, 2020
Priority date	Jul 8, 2020
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.

First claim

What is claimed is:

1. A heat engine defining a forward direction and an aft direction, the heat engine comprising:
a compressor section;
a turbine section positioned aft of the compressor section;
a rotor assembly comprising a rotor disk and a seal assembly;
an interfacing structure at least partially surrounding the rotor assembly at the seal assembly, wherein the seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition; and
a fluid supply manifold connected to the rotor assembly, the fluid supply manifold comprising an inlet opening at the first cavity and an outlet opening at the rotor disk, wherein the inlet opening is positioned aft of the seal assembly,
wherein the fluid supply manifold is extended, at least partially along a radial direction, from the inlet opening at the first cavity to the outlet opening at the rotor disk,
wherein the outlet opening is adjacent the rotor disk such that a fluid flowing through the fluid supply manifold is in thermal communication with at least an inner portion in the radial direction of the rotor disk of the rotor assembly, and
wherein aft is defined as a downstream direction relative to a gas flow through the compressor section and the turbine section.

2. The heat engine of claim 1 , wherein the fluid supply manifold comprises:
a first manifold portion extended along the radial direction, wherein the first manifold portion comprises the inlet opening in fluid communication with the first cavity;
a second manifold portion extended along an axial direction; and
a third manifold portion extended along the radial direction, wherein the third manifold portion comprises the outlet opening in fluid communication with the rotor disk of the rotor assembly.

3. The heat engine of claim 2 , wherein the third manifold portion is positioned inward of the rotor disk along the radial direction.

4. The heat engine of claim 2 , wherein the fluid supply manifold comprises a plurality of the third manifold portion arranged in circumferential arrangement relative to one another.

5. The heat engine of claim 2 , wherein the fluid supply manifold comprises a plurality of the first manifold portion arranged in circumferential arrangement relative to one another.

6. The heat engine of claim 5 , wherein a fluid pathway is formed between adjacent pairs of the plurality of the first manifold portion arranged in circumferential arrangement.

7. The heat engine of claim 2 , wherein the heat engine forms a first plenum adjacent to a first side of the rotor disk, a second plenum adjacent to a second side of the rotor disk opposite of the first side of the rotor disk, wherein the second plenum is formed between the rotor disk and the seal assembly, and wherein the heat engine forms a third plenum adjacent to the seal assembly opposite of the second plenum.

8. The heat engine of claim 7 , wherein a fluid pathway is formed between adjacent pairs of a plurality of the first manifold portion arranged in circumferential arrangement, and wherein the fluid pathway provides fluid communication between the second plenum and the third plenum.

9. The heat engine of claim 8 , wherein the fluid supply manifold comprising the plurality of the first manifold portion forms a fluid flowpath from the first cavity to the outlet opening, and wherein the fluid supply manifold fluidly separates the fluid flowpath from the second plenum and the third plenum.

10. The heat engine of claim 1 , wherein the outlet opening is positioned in fluid impingement relationship with the rotor disk.

11. The heat engine of claim 1 , wherein the seal assembly comprises a compressor discharge pressure seal positioned between the compressor section and the turbine section.

12. The heat engine of claim 11 , wherein the rotor disk is positioned at the compressor section.

13. The heat engine of claim 11 , wherein the rotor assembly comprises a shaft extended to the compressor section and the turbine section, and wherein the fluid supply manifold is coupled to the shaft.

14. The heat engine of claim 11 , wherein the first cavity is positioned distal to the compressor section, and wherein the second cavity is positioned proximate to the compressor section relative to the first cavity.

15. A heat engine comprising:
a compressor section;
a turbine section positioned aft of the compressor section;
a rotor assembly comprising a rotor disk and a seal assembly;
an interfacing structure at least partially surrounding the rotor assembly at the seal assembly, wherein the seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition; and
a fluid supply manifold connected to the rotor assembly, the fluid supply manifold comprising an inlet opening at the first cavity and an outlet opening at the rotor disk, wherein the inlet opening is positioned aft of the seal assembly,
wherein the fluid supply manifold is extended, at least partially along a radial direction, from the inlet opening at the first cavity to the outlet opening at the rotor disk,
wherein the outlet opening is adjacent the rotor disk such that a fluid flowing through the fluid supply manifold is in thermal communication with at least an inner portion in the radial direction of the rotor disk of the rotor assembly,
wherein the fluid supply manifold comprises:
a first manifold portion extended along the radial direction, wherein the first manifold portion comprises the inlet opening in fluid communication with the first cavity;
a second manifold portion extended along an axial direction; and
a third manifold portion extended along the radial direction, wherein the third manifold portion comprises the outlet opening in fluid communication with the rotor disk of the rotor assembly,

wherein the heat engine forms a first plenum adjacent to a first side of the rotor disk, a second plenum adjacent to a second side of the rotor disk opposite of the first side of the rotor disk, wherein the second plenum is formed between the rotor disk and the seal assembly, and wherein the heat engine forms a third plenum adjacent to the seal assembly opposite of the second plenum,
wherein the fluid supply manifold is configured to provide a first fluid to an area including the first plenum and the second plenum, and a fluid flowpath is configured to provide a second fluid to the area including the first plenum and the second plenum, and
wherein the first fluid is received from a first location along a gas flowpath and the second fluid is received from a second location of the gas flowpath such that the first fluid has at least one of a higher temperature and a higher pressure than the second fluid.

16. The heat engine of claim 15 , wherein the first fluid is from a first stage of the compressor section and the second fluid is from a second stage of the compressor section, wherein the first stage is downstream from the second stage.

17. The heat engine of claim 15 , wherein the first fluid is compressor discharge pressure air or Station 3 flow path air.

18. The heat engine of claim 15 , wherein the outlet opening of the fluid supply manifold is limited to an aftmost end of the rotor assembly, the aftmost end of the rotor assembly including the rotor disk.

19. A heat engine defining a radial direction that extends from a centerline axis of the heat engine, the heat engine comprising:
a rotor

Assignees

• Gen Electric

Inventors

• Namadevan Arvind
• Rambo Jeffrey Douglas
• Sen Arnab

Classifications

• F01D5/082

  on the side of the rotor disc · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/084 Primary

  the fluid circulating at the periphery of a multistage rotor, e.g. of drum type · CPC title