Adjustable flow split platform cooling for gas turbine engine

Patent metadata

Field	Value
Publication number	US-2018347397-A1
Application number	US-201715613686-A
Country	US
Kind code	A1
Filing date	Jun 5, 2017
Priority date	Jun 5, 2017
Publication date	Dec 6, 2018
Grant date	—

Abstract

A turbine assembly may comprise a platform defining a platform cavity cooled by a platform flow with a vane extending from the platform. A platform-fed through cavity is defined by the vane and cooled by a first portion of the platform flow. A direct-fed through flow cavity is defined in the vane and cooled by a direct-fed through flow. The direct-fed through flow cavity and the platform-fed through cavity meet at an outlet to expel an outgoing through flow from the outlet. A platform-fed serpentine cavity may be defined in the vane and separated from the platform-fed through cavity by a divider. The platform-fed serpentine cavity is cooled by a second portion of the platform flow.

First claim

What is claimed is:

1 . A turbine assembly comprising:
a platform defining a platform cavity cooled by a platform flow; a vane extending from the platform; a platform-fed through cavity defined by the vane and cooled by a first portion of the platform flow; a direct-fed through cavity defined by the vane and cooled by a through flow, wherein the direct-fed through cavity and the platform-fed through cavity meet at an outlet to expel an outgoing through flow from the outlet; and a platform-fed serpentine cavity defined by the vane and separated from the platform-fed through cavity by a divider, wherein the platform-fed serpentine cavity is cooled by a second portion of the platform flow.

2 . The turbine assembly of claim 1 , further comprising a blade aft of the vane, wherein the blade is cooled by the outgoing through flow.

3 . The turbine assembly of claim 1 , further comprising a trailing edge cavity in fluid communication with the platform-fed serpentine cavity.

4 . The turbine assembly of claim 3 , wherein the second portion of the platform flow is exhausted from the trailing edge cavity into a core flow.

5 . The turbine assembly of claim 1 , wherein the through flow and the first portion of the platform flow mix at the outlet to form the outgoing through flow.

6 . The turbine assembly of claim 1 , wherein the platform-fed through cavity is in fluid communication with the platform cavity.

7 . The turbine assembly of claim 1 , wherein the through flow is extracted from a compressor stage of a gas turbine engine.

8 . A gas turbine engine comprising:
a compressor configured to compress a core flow; a combustor in fluid communication with the compressor and configured to combust the core flow; a turbine aft of the combustor and configured to expand the core flow, the turbine comprising:
a platform defining a platform cavity having a platform-fed flow exiting the platform;
a vane extending from the platform;
a platform-fed through cavity defined by the vane and cooled by a first portion of the platform-fed flow;
a direct-fed through cavity defined by the vane and cooled by a through flow, wherein the direct-fed through cavity and the platform-fed through cavity meet at an outlet; and a platform-fed serpentine cavity defined by the vane and separated from the platform-fed through cavity, wherein the platform-fed serpentine cavity is cooled by a second portion of the platform-fed flow.

9 . The gas turbine engine of claim 8 , further comprising a blade aft of the vane in the turbine, wherein the blade is cooled by the outgoing through flow.

10 . The gas turbine engine of claim 8 , further comprising a trailing edge cavity in fluid communication with the platform-fed serpentine cavity.

11 . The gas turbine engine of claim 10 , wherein the second portion of the platform-fed flow is exhausted from the trailing edge cavity into the core flow.

12 . The gas turbine engine of claim 8 , wherein the through flow and the first portion of the platform-fed flow mix at the outlet to form the outgoing through flow.

13 . The gas turbine engine of claim 8 , wherein the platform-fed through cavity in fluid communication with the platform cavity.

14 . The gas turbine engine of claim 8 , wherein the through flow is bled from the core flow in the compressor.

15 . A vane comprising:
a vane platform defining a platform cavity; a platform-fed through cavity defined by the vane and in fluid communication with the platform cavity; a direct-fed through cavity defined by the vane, wherein the direct-fed through cavity and the platform-fed through cavity meet at an outlet; and a platform-fed serpentine cavity defined by the vane and separated from the platform-fed through cavity by a divider, wherein the platform-fed serpentine cavity is in fluid communication with the platform cavity.

16 . The vane of claim 15 , further comprising a trailing edge cavity in fluid communication with the platform-fed serpentine cavity.

17 . The vane of claim 16 , wherein the trailing edge cavity is configured to exhaust a platform-fed flow.

18 . The vane of claim 15 , wherein the outlet is configured to mix a through flow from the direct-fed through cavity and a platform-fed flow from the platform-fed through cavity.

19 . The vane of claim 15 , wherein the platform-fed through cavity and the platform-fed serpentine cavity are cooled by a platform-fed flow exiting the platform cavity.

20 . The vane of claim 15 , wherein the direct-fed through cavity is cooled by a direct cooling source.

Assignees

• United Technologies Corp

Inventors

• Clum Carey
• Generale Adam

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D25/12 Primary

  Cooling · CPC title