Heat shield manifold system for a midframe case of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9714611-B2
Application number	US-201313768038-A
Country	US
Kind code	B2
Filing date	Feb 15, 2013
Priority date	Feb 15, 2013
Publication date	Jul 25, 2017
Grant date	Jul 25, 2017

Abstract

A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.

First claim

We claim:

1. A turbine engine, comprising:
at least one combustor positioned upstream from a rotor assembly, wherein
the rotor assembly includes at least first and second rows of turbine blades extending radially outward from a rotor;
a compressor positioned upstream from the at least one combustor;
at least one row of turbine vanes extending radially inward and terminating proximate to the rotor assembly;
an inner case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly;
a heat shield wall positioned radially outward of the inner case and circumferentially encapsulating the inner case, thereby forming a heat shield manifold on an outer surface of the inner case;
a turbine airfoil cooling chamber in communication with turbine airfoils, wherein the turbine airfoil cooling chamber extends downstream of an end of the inner case and an end of the heat shield wall;
a support extending radially outward from the inner case and supporting the heat shield wall; and
a compressor bleed exhaust in communication with the heat shield wall whereby the compressor bleed exhaust supplies cooling fluid to the heat shield manifold and is in communication with a turbine airfoil cooling chamber such that the heat shield manifold supplies cooling fluid to the turbine airfoil cooling chamber.

2. The turbine engine of claim 1 , wherein the turbine airfoil cooling chamber is a turbine vane row two cooling air chamber that provides cooling fluid to row two turbine vanes.

3. The turbine engine of claim 1 , further comprising an outer case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly and circumferentially encapsulating the heat shield wall.

4. The turbine engine of claim 1 , further comprising a jumper conduit extending between the compressor and the heat shield manifold.

5. The turbine engine of claim 4 , further comprising a heat exchanger configured to chill cooling fluid from the compressor before the cooling fluid is passed to the heat shield manifold.

6. The turbine engine of claim 4 , further comprising a bleed exhaust conduit extending between the compressor and the turbine airfoil cooling chamber.

7. The turbine engine of claim 6 , further comprising at least one jumper throttle system configured to dynamically throttle compressor bleed fluid into the jumper conduit.

8. The turbine engine of claim 7 , further comprising at least one airfoil cooling chamber throttle system configured to dynamically throttle compressor bleed fluid into the turbine airfoil cooling chamber.

9. The turbine engine of claim 7 , wherein the at least one jumper throttle system is at least one valve controlling the flow of cooling fluid through the jumper conduit.

10. The turbine engine of claim 6 , further comprising at least one airfoil cooling chamber throttle system configured to dynamically throttle compressor bleed fluid into the turbine airfoil cooling chamber.

11. The turbine engine of claim 10 , wherein the at least one airfoil cooling chamber throttle system is at least one valve controlling the flow of cooling fluid through the bleed exhaust conduit into the turbine airfoil cooling chamber.

12. The turbine engine of claim 4 , wherein the jumper conduit extends at least partially externally of an outer case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly and circumferentially encapsulating the heat shield wall.

13. The turbine engine of claim 1 , further comprising a bleed exhaust conduit extending between the compressor and the turbine airfoil cooling chamber;
wherein the bleed exhaust conduit extends at least partially externally of an outer case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly and circumferentially encapsulating the heat shield wall.

14. The turbine engine of claim 1 , wherein the heat shield manifold is in communication with the compressor through at least one orifice in a support flange radially inward of an outer case, which eliminates a possibility of flange to flange leakage.

15. A turbine engine, comprising:
at least one combustor positioned upstream from a rotor assembly, wherein
the rotor assembly includes at least first and second rows of turbine blades extending radially outward from a rotor;
a compressor positioned upstream from the at least one combustor;
at least one row of turbine vanes extending radially inward and terminating proximate to the rotor assembly;
an inner case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly;
a heat shield wall positioned radially outward of the inner case and circumferentially encapsulating the inner case, thereby forming a heat shield manifold on an outer surface of the inner case;
a turbine airfoil cooling chamber in communication with turbine airfoils, wherein the turbine airfoil cooling chamber extends downstream of an end of the inner case and an end of the heat shield wall;
a support extending radially outward from the inner case and supporting the heat shield wall;
an outer case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly and circumferentially encapsulating the heat shield wall;
a compressor bleed exhaust in communication with the heat shield wall whereby the compressor bleed exhaust supplies cooling fluid to the heat shield manifold and is in communication with a turbine airfoil cooling chamber such that the heat shield manifold supplies cooling fluid to the turbine airfoil cooling chamber; and
wherein the turbine airfoil cooling chamber is a turbine vane row two cooling air chamber that provides cooling fluid to row two turbine vanes.

16. The turbine engine of claim 15 , further comprising a jumper conduit extending between the compressor and the heat shield manifold, wherein the jumper conduit extends at least partially externally of an outer case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly and circumferentially encapsulating the heat shield wall.

17. The turbine engine of claim 15 , further comprising a heat exchanger configured to chill cooling fluid from the compressor before the cooling fluid is passed to the heat shield manifold.

18. The turbine engine of claim 15 , further comprising a bleed exhaust conduit extending between the compressor and the turbine airfoil cooling chamber,
wherein the bleed exhaust conduit extends at least partially externally of an outer case extending from a downstream end region of the compressor to an upstream end region of the rotor assembly and circumferentially encapsulating the heat shield wall.

19. The turbine engine of claim 18 , further comprising at least one jumper throttle system configured to dynamically throttle compressor bleed fluid into the jumper conduit, and at least one airfoil cooling chamber throttle system configured to dynamically throttle compressor bleed fluid into the turbine airfoil cooling chamber.

20. The turbine engine of claim 15 , wherein the heat shield manifold is in communication with the compressor through at least one orifice in a support flange radially inward of an outer case, which eliminates a possibility of flange to flange leakage.

Assignees

• Mayer Clinton A
• Eng Jesse
• Schopf Cheryl A
• Siemens Energy Inc

Inventors

• Mayer Clinton A
• Eng Jesse
• Schopf Cheryl A

Classifications

• F02C7/12 Primary

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title