Overcooled air cooling system with annular mixing passage

Patent metadata

Field	Value
Publication number	US-2016208703-A1
Application number	US-201514600862-A
Country	US
Kind code	A1
Filing date	Jan 20, 2015
Priority date	Jan 20, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.

First claim

What is claimed is:

1 . A cooling system, comprising:
a heat exchanger; a first conduit fluidly coupled to an inlet of the heat exchanger; a second conduit fluidly coupled to an outlet of the heat exchanger; an annular passage fluidly coupled to the second conduit; and a tangential onboard injector (TOBI) fluidly coupled to the annular passage.

2 . The cooling system of claim 1 , wherein the second conduit comprises a tube having a double walled architecture.

3 . The cooling system of claim 1 , further comprising mixing openings defined by a distal surface of the annular passage.

4 . The cooling system of claim 3 , further comprising a diffuser having a proximal boundary at least partially defined by the distal surface of the annular passage.

5 . The cooling system of claim 4 , further comprising a first conduit fluidly coupled to the diffuser and an inlet of the heat exchanger.

6 . The cooling system of claim 5 , wherein the first conduit is configured to extract 0.5 to 20 percent of air available in the diffuser.

7 . The cooling system of claim 5 , the second conduit is longer than the first conduit.

8 . A gas turbine engine, comprising:
a compressor; a combustor in fluid communication with the compressor; a turbine in fluid communication with the combustor; a diffuser around the combustor; a first conduit fluidly coupled to the diffuser; a heat exchanger comprising an inlet fluidly coupled to the first conduit; a second conduit fluidly coupled to an outlet of the heat exchanger; an annular passage fluidly coupled to the second conduit; and a tangential onboard injector (TOBI) fluidly coupled to the annular passage.

9 . The gas turbine engine of claim 8 , wherein the second conduit comprises a tube having a double walled architecture.

10 . The gas turbine engine of claim 8 , further comprising mixing openings defined by a distal surface of the annular passage.

11 . The gas turbine engine of claim 10 , wherein the distal surface of the annular passage at least partially defines a boundary of the diffuser.

12 . The gas turbine engine of claim 8 , wherein the first conduit is configured to extract air from the diffuser.

13 . The gas turbine engine of claim 8 , wherein the first conduit is configured to extract 0.5 to 20 percent of air available in the diffuser.

14 . The gas turbine engine of claim 12 , the second conduit is longer than the first conduit.

15 . A diffuser case, comprising:
a first conduit configured to extract gas from the diffuser case; a second conduit in fluid communication with the first conduit and comprising a double walled architecture, wherein the second conduit extends through the diffuser case; and an annular passage at least partially defining a proximal boundary of the diffuser case, the annular passage in fluid communication with the second conduit.

16 . The diffuser case of claim 15 , wherein the first conduit is configured to extract 0.5 to 20 percent of air available in the diffuser case.

17 . The diffuser case of claim 15 , wherein the first conduit is longer than the second conduit.

18 . The diffuser case of claim 15 , further comprising mixing openings defined by a wall of the annular passage.

19 . The diffuser case of claim 18 , wherein the annular passage is configured to operate as an ejector with the mixing openings.

20 . The diffuser case of claim 15 , wherein the second conduit comprises a nickel-based superalloy.

Assignees

• United Technologies Corp

Inventors

• Hill James D
• Ackermann William K

Classifications

• F23R3/045

  using pipes · CPC title

• F01D5/082 Primary

  on the side of the rotor disc · CPC title

• F05D2260/211

  by intercooling, e.g. during a compression cycle · CPC title

• F05D2260/209

  using vortex tubes · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title