Downstream turbine vane cooling for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11021981-B2
Application number	US-201815985852-A
Country	US
Kind code	B2
Filing date	May 22, 2018
Priority date	May 22, 2018
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A gas turbine engine includes a main compressor section and a turbine section. The turbine section has a first turbine blade and vane and a downstream turbine component. A tap is configured to tap air from the compressor section at a location upstream of a most downstream location. The tap is connected to a heat exchanger. The heat exchanger is connected to a cooling compressor. The cooling compressor is connected to the downstream turbine component. A second tap is configured to tap air from a location in the main compressor section. The second tap is connected through a check valve to a line leading to the downstream turbine component. A control operates the cooling compressor such that when the cooling compressor is operating, air downstream of the cooling compressor is at a pressure higher than the pressure of the second tap, and the control is operational to selectively drive the cooling compressor at high power operation of an associated gas turbine engine, and to stop operation of the cooling compressor at lower power operations, such that air is delivered through the cooling compressor to the downstream turbine component at the high power operations, and air is delivered from the second tap at least some time when the cooling compressor is not operational. A method is also disclosed.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a main compressor section and a turbine section, said turbine section having a first turbine blade and vane and a downstream turbine component;
a tap configured to tap air from said compressor section at a location upstream of a most downstream location, and said tap connected to a heat exchanger, the heat exchanger connected to a cooling compressor, and the cooling compressor connected to said downstream turbine component;
a second tap configured to tap air from a location in said main compressor section, and said second tap connected through a check valve to a line leading to said downstream turbine component; and
a control for operating said cooling compressor such that when said cooling compressor is operating, air downstream of said cooling compressor is at a pressure higher than the pressure of air from said second tap, and said control being operational to selectively drive said cooling compressor at high power operation of the gas turbine engine, and to stop operation of said cooling compressor at lower power operations, such that air is delivered through said cooling compressor to said downstream turbine component at the high power operation, and air is delivered from said second tap at least some time when said cooling compressor is not operational;
wherein a first controlled valve is provided intermediate said cooling compressor and said downstream turbine component and may be closed to block flow downstream of the cooling compressor by said control; and
wherein a second controlled valve is positioned between said second tap and said downstream turbine component, with said controlled valve also being controlled by said control to selectively block flow to the downstream turbine component.

2. The gas turbine engine as set forth in claim 1 , wherein said second tap is connected to said first tap.

3. The gas turbine engine as set forth in claim 1 , wherein said downstream turbine component is a second stage turbine vane.

4. The gas turbine engine as set forth in claim 1 , wherein at the high power operation said second controlled valve on said second tap is closed and said cooling compressor is operated and said first controlled valve is open such that high pressure air from the cooling compressor is delivered to said downstream turbine component.

5. The gas turbine engine as set forth in claim 4 , wherein in a first intermediate mode stage, both said first and second controlled valves are opened and said cooling compressor is stopped such that air is delivered from both said first and second taps to said downstream turbine component.

6. The gas turbine engine as set forth in claim 5 , wherein in a second intermediate cooling mode, said first controlled valve is closed, said cooling compressor is stopped, and said second controlled valve is opened such that air is only delivered from said second tap to the downstream turbine component.

7. The gas turbine engine as set forth in claim 6 , wherein in a lower cooling mode, said second controlled valve is closed, said cooling compressor is stopped and said first controlled valve is open such that only air downstream of the cooling compressor, which has not been compressed by the cooling compressor, is delivered to the downstream turbine component.

8. The gas turbine engine as set forth in claim 5 , wherein air downstream of said first and second controlled valves connects into a common line passing to said downstream turbine component.

9. A method of operating a gas turbine engine including the steps of:
tapping a first air flow from a main compressor section at a location upstream of a most downstream location, and passing said first air flow to a heat exchanger, and then to a cooling compressor, passing air downstream of the cooling compressor to a turbine component at a downstream location in a turbine section; and
tapping a second air flow from a location in said main compressor section, and passing the second air flow through a check valve to a line leading to said turbine component, and operating said cooling compressor such that when said cooling compressor is operating, said first air flow is at a pressure higher than the pressure of said second air flow, and operating said cooling compressor at high power operation, and stopping operation of said cooling compressor at lower power conditions, such that the first air flow is delivered from said cooling compressor to said turbine component at the high power operation, and the second air flow is delivered at least at some times when said cooling compressor is not operational;
wherein a first controlled valve is provided intermediate said cooling compressor and said turbine component and is closed to block flow downstream of the cooling compressor;
wherein a second controlled valve is positioned to block said second air flow to said turbine component; and
wherein at highest power operation said second controlled valve is closed and said cooling compressor is operated and said first controlled valve is open such that the first air flow from the cooling compressor is delivered to said turbine component.

10. The method of operating a gas turbine engine as set forth in claim 9 , wherein said turbine component is a second stage turbine vane.

11. The method of operating a gas turbine engine as set forth in claim 9 , wherein in a first intermediate mode stage, both said first and second controlled valves are opened and said cooling compressor is stopped such that both said first and second airflows flow to said turbine component.

12. The method of operating a gas turbine engine as set forth in claim 9 , wherein in a second intermediate cooling mode, said first controlled valve is closed, said cooling compressor is stopped, and said second controlled valve is opened such that said second air flow is delivered to the turbine component.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Schwarz Frederick M

Classifications

• F01D9/048

  for radial admission · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F05D2270/3062

  of the auxiliary fluid for heating or cooling purposes · CPC title

• F02C7/143

  before or between the compressor stages · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title