Impingement-cooled turbine rotor

Patent metadata

Field	Value
Publication number	US-9476305-B2
Application number	US-201313892828-A
Country	US
Kind code	B2
Filing date	May 13, 2013
Priority date	May 13, 2013
Publication date	Oct 25, 2016
Grant date	Oct 25, 2016

Abstract

An integral turbine includes a forward hub section and an aft hub section. The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.

First claim

What is claimed is:

1. An integral turbine rotor comprising:
a forward hub section;
an aft hub section, wherein the forward hub section and the aft hub section are coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the integral turbine rotor;
an airfoil blade ring, which comprises a plurality of integral blades, which are circumferentially spaced around and extend radially outward of the coupled forward and after hub sections, coupled to a radial outer surface of the coupled forward and aft hub sections;
an impingement cavity formed within an interior portion of the coupled forward and aft hub sections, wherein the impingement cavity comprises an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections;
an impingement air flow channel in fluid communication with the impingement cavity, wherein cooling air is accelerated and narrowed as it flows through the impingement air flow channel to produce the impingement cooling air flow;
an internal hub cavity formed within an interior portion of the coupled forward and aft hub section that is in fluid communication with the impingement air flow channel, wherein cooling air flows from the internal hub cavity into the impingement air flow channel, wherein the internal hub cavity is positioned radially-inward from the impingement cavity within the interior portion of the coupled forward and aft hub section, wherein the impingement air flow channel has an axial width that is less than a greatest axial width of both the impingement cavity and the internal hub cavity, and wherein the impingement air flow channel provides fluid connection between the internal hub cavity and the impingement cavity,
wherein an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections; and
a central opening located radially inward from the internal hub cavity, and a hub cooling air passage, wherein the hub cooling air passage has an axial width that is less than a greatest axial width of both the impingement cavity and the internal hub cavity, and wherein the hub cooling air passage provides fluid connection between the central opening and the internal hub cavity.

2. The integral turbine rotor similar to claim 1 , further comprising a second airfoil blade spaced apart from the first airfoil blade and each metallurgically coupled to the radial outer surface of the coupled forward and aft hub section, wherein the interior surface of the impingement cavity is positioned proximate to a portion of the radial outer surface in between the first and second airfoil blades.

3. The integral turbine rotor of claim 1 , wherein the interior surface of the impingement cavity is positioned proximate to an axially mid portion of the outer surface of the coupled forward and aft hub section.

4. The integral turbine rotor of claim 3 , wherein the impingement cavity is positioned along the annular interface where the forward and the aft hub sections are coupled.

5. The integral turbine rotor of claim 1 , further comprising an impingement air flow channel in fluid communication with the impingement cavity, wherein cooling air is accelerated and narrowed as it flows through the impingement air flow channel to produce the impingement cooling air flow.

6. The integral turbine rotor of claim 5 , wherein the impingement air flow channel is positioned along the annular interface where the forward and the aft hub sections are coupled.

7. The integral turbine of claim 5 , further comprising an internal hub cavity in fluid communication with the impingement air flow channel, wherein cooling air flows from the internal hub cavity into the impingement air flow channel.

8. The integral turbine of claim 7 , wherein the internal hub cavity is positioned radially inward from the impingement cavity.

9. The integral turbine rotor of claim 1 , wherein the turbine is a radial flow turbine.

10. The integral turbine of claim 1 , wherein the turbine is an axial flow turbine.

11. The integral turbine rotor of claim 1 , wherein the airfoil blade ring comprises a single, integrally-fabricated component.

12. The integral turbine rotor of claim 1 , further comprising a cooling air flow exit channel in fluid communication with the impingement cavity and extending between the impingement cavity and the radial outer surface of the coupled forward and aft hub sections, wherein cooling air flow exits the turbine through the cooling air flow exit channel subsequent to impinging upon the interior surface of the impingement cavity.

13. The integral turbine of claim 1 , wherein the first airfoil blade comprises an internal blade cooling circuit in fluid communication with the impingement cavity, wherein cooling air flow enters the internal blade cooling circuit subsequent to impinging upon the interior surface of the impingement cavity to provide a cooling flow within the first airfoil blade.

14. The integral turbine rotor of claim 1 , where the forward hub section comprises a first metal alloy and the aft hub section comprises a second metal alloy that is either different from or identical to the first metal alloy.

15. The integral turbine of claim 1 , wherein the impingement cavity comprises a generally circular, elliptical, or ovoid radial cross-section.

16. The integral turbine of claim 1 , further comprising an axially-oriented central opening in fluid communication with the internal hub cavity for providing cooling air thereto.

17. The integral turbine of claim 1 , wherein the axially-oriented central opening is in fluid communication with a compressor bypass duct for providing compressor bypass air as the cooling air.

18. The integral turbine rotor of claim 1 , where the impingement cavity is one cavity.

19. The integral turbine rotor of claim 1 , where the impingement cavity comprises multiple cavities.

20. The integral turbine rotor of claim 1 , wherein the second airfoil blade comprises an internal blade cooling circuit in fluid communication with the impingement cavity, wherein cooling air flow enters the internal blade cooling circuit subsequent to impinging upon the interior surface of the impingement cavity to provide a cooling flow within the second airfoil blade.

Assignees

• Honeywell Int Inc

Inventors

• Jan David K
• Miner Amandine

Classifications

• F01D5/3061

  by welding, brazing · CPC title

• F01D5/045

  the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/087

  in the radial passages of the rotor disc · CPC title