Thermal gradient attenuation structure to mitigate rotor bow in turbine engine

Patent metadata

Field	Value
Publication number	US-10947993-B2
Application number	US-201715822507-A
Country	US
Kind code	B2
Filing date	Nov 27, 2017
Priority date	Nov 27, 2017
Publication date	Mar 16, 2021
Grant date	Mar 16, 2021

Abstract

Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal circuit at the second manifold assembly.

First claim

What is claimed is:

1. A gas turbine engine defining an axial centerline and a longitudinal direction extended co-directional thereto and a radial direction extended from the axial centerline, the engine comprising:
a rotor assembly comprising a shaft extended along the longitudinal direction, wherein a compressor rotor and a turbine rotor are each coupled to the shaft;
a casing surrounding the rotor assembly, wherein the casing defines a first opening positioned directly outward of the turbine rotor in the radial direction, and a second opening positioned directly outward of the compressor rotor in the radial direction;
a first manifold assembly coupled to the casing at the first opening;
a second manifold assembly coupled to the casing at the second opening, wherein the first manifold assembly, the casing, and the second manifold assembly together define a thermal circuit in thermal communication with the rotor assembly; and
a fluid flow device in fluid communication with the first manifold assembly,
wherein the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and
further wherein the flow of fluid egresses from the thermal circuit at the second manifold assembly.

2. The gas turbine engine of claim 1 , wherein the fluid flow device is further in fluid communication with the second manifold assembly such as to define a substantially closed circuit fluid communication of the thermal circuit.

3. The gas turbine engine of claim 1 , wherein the fluid flow device defines a compressor system providing a pressurized flow of fluid to the first manifold assembly.

4. The gas turbine engine of claim 1 , wherein the first opening is defined at the casing within approximately +/−90 degrees relative to top dead center from the axial centerline of the engine.

5. The gas turbine engine of claim 1 , wherein the second opening is at the casing defined within approximately +/−90 degrees relative to top dead center from the axial centerline of the engine.

6. The gas turbine engine of claim 1 , wherein the second opening is defined at the casing within approximately 90 degrees to approximately 270 degrees relative to top dead center from the axial centerline of the engine.

7. The gas turbine engine of claim 1 , wherein the second opening is defined at the casing within approximately 225 degrees to approximately 315 degrees relative to top dead center from the axial centerline of the engine.

8. The gas turbine engine of claim 1 , wherein the fluid flow device is coupled to the first manifold assembly and the second manifold assembly.

9. The gas turbine engine of claim 8 , further defining a serial flow arrangement of the first manifold assembly, the fluid flow device, and the second manifold assembly.

10. The gas turbine engine of claim 8 , further defining a closed circuit serial flow arrangement of the casing, first manifold assembly, the fluid flow device, the second manifold assembly, and the casing.

11. The gas turbine engine of claim 1 , wherein the rotor assembly defines a vent opening in fluid communication with the thermal circuit.

12. The gas turbine engine of claim 11 , further comprising:
a wall assembly coupled to the rotor assembly, the casing, or both, wherein the wall assembly comprises a moveable joint coupled to a wall, and wherein the moveable joint translates the wall to and from the vent opening at the rotor assembly, the second opening at the casing, or both.

13. The gas turbine engine of claim 12 , wherein the moveable joint of the wall assembly defines a guided rail coupled to the wall, wherein the guided rail translates the wall to and from the vent opening at the rotor assembly, the second opening at the casing, or both.

14. The gas turbine engine of claim 12 , wherein the moveable joint of the wall assembly defines a hinge coupled to the wall, wherein the hinge translates the wall to and from the vent opening at the rotor assembly, the second opening at the casing, or both.

15. The gas turbine engine of claim 1 , further comprising:
a valve assembly directing the flow of fluid in a first direction and mitigating a flow of fluid in a second direction opposite of the first direction.

16. The gas turbine engine of claim 1 , wherein at least one of the first opening or the second opening defines a borescope port or a bleed port at the casing of the gas turbine engine.

17. The gas turbine engine of claim 1 , wherein the fluid flow device provides an intermittent or continuous flow of fluid through the thermal circuit.

18. The gas turbine engine of claim 1 , wherein the flow of fluid defines a flow of air, water, an inert gas, or combinations thereof.

Assignees

• Gen Electric

Inventors

• Shinde Kudum
• Sharma Praveen
• Puranik Shashank Suresh
• Mittal Shivam
• Orkiszewski Charles Stanley
• Macmahon Carl Lawrence
• Metz Anthony Michael
• Drummond Brian

Classifications

• F04D27/0223

  Control schemes therefor · CPC title

• F01D25/10

  Heating, e.g. warming-up before starting · CPC title

• F01D19/02

  dependent on temperature of component parts, e.g. of turbine-casing · CPC title

• F05D2260/608

  Aeration, ventilation, dehumidification or moisture removal of closed spaces · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title