Active control of bucket cooling supply for turbine

Patent metadata

Field	Value
Publication number	US-9316152-B2
Application number	US-201213495306-A
Country	US
Kind code	B2
Filing date	Jun 13, 2012
Priority date	Jun 13, 2012
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A cooling gas flow control device for a turbine rotor that is internally located between the compressor and the turbine section of a turbine is disclosed. The cooling gas flow control device has a shape memory material that is used to actively adjust the cooling gas flow to internal parts of the turbine section between, including the buckets.

First claim

The invention claimed is:

1. A cooling gas flow control device for a turbine rotor comprising:
a. an internal cooling gas pathway located between an outlet of a compressor section and an inlet for an internal turbine cavity of a turbine section; and
b. an adjustable gas flow valve located between the outlet of the compressor and the inlet for the rotor cavity in the cooling gas pathway, the adjustable gas flow valve including:
a mount,
a plurality of shape memory materials each having a first end and a second end, wherein the mount is connected to one of the plurality of shape memory materials at the first end thereof, and
a unitary flow restrictor connected to the second end of each of the plurality of the shape memory materials;

wherein the adjustable gas flow valve adjusts gas flow rate through the cooling gas pathway based on a physical parameter of compressed gas exiting the compressor section of the turbine.

2. The cooling gas flow control device according to claim 1 , wherein one of the plurality of shape memory materials comprises a shape memory alloy.

3. The cooling gas flow control device according to claim 1 , wherein one of the plurality of shape memory materials comprises a channel through the shape memory material, and the channel is adapted to receive gas from the compressor section.

4. The cooling gas flow control device according to claim 1 , wherein the unitary flow restrictor comprises an accordion-like structure.

5. The cooling gas flow control device according to claim 1 , wherein the unitary flow restrictor comprises a valve disc positioned in a hole of a connecting wheel, where the connecting wheel is positioned between and joins the compressor section and the turbine section of the turbine.

6. The cooling gas flow control device according to claim 5 , wherein the mount is positioned in a recess located adjacent an aperture in the connecting wheel.

7. The cooling gas flow control device according to claim 1 , wherein one of the plurality of shape memory materials is formed in segments that change shape to reduce flow rate through the adjustable gas flow valve.

8. The cooling gas flow control device according to claim 7 , wherein the one of the plurality of shape memory materials changes between a cylindrical shape to a truncated conical shape to adjust the gas flow through the adjustable gas flow valve.

9. The cooling gas flow control device according to claim 1 , wherein the cooling gas pathway is located in a connecting wheel which connects a compressor section and the turbine section of a gas turbine.

10. The cooling gas flow control device according to claim 1 , wherein one of the plurality of shape memory materials comprises multiple different shape memory segments, wherein each segment has a different transition temperature.

11. A method of controlling cooling gas for a rotor cavity of a turbine rotor comprising
a. drawing cooling gas from a compressor of a turbine, said cooling gas having a temperature;
b. directing the cooling gas into an internal pathway connecting the compressor and a rotor cavity of turbine rotor,
c. passing the cooling gas in the internal pathway through an adjustable gas flow valve, the adjustable gas flow valve including:
a mount,
a plurality of shape memory materials each having a first end and a second end, wherein the mount is connected to one of the plurality of shape memory materials at the first end thereof, and
a unitary flow restrictor connected to the second end of each of the plurality of the shape memory materials;

wherein each of the plurality of shape memory materials changes shape based on an input temperature to the plurality of shape memory materials to adjust the flow of the cooling gas through the internal pathway to the cavity of the turbine rotor.

12. The method according to claim 11 , wherein the compressor has a compressed gas discharged there from, said compressed gas having a temperature, and the input temperature is the temperature of compressed gas being discharged from the compressor.

13. The method according to claim 12 , wherein the adjustable gas flow valve comprises a channel through the plurality of shape memory materials, and the compressed gas is passed through the channel with the plurality of shape memory materials responding to the temperature of the compressed gas passed through the channel.

14. The method according to claim 11 , wherein the input temperature is the temperature of the cooling gas being directed into the internal pathway.

15. The method according to claim 14 , wherein the adjustable gas flow valve comprises a channel through the plurality of shape memory materials, and the cooling gas is passed through the channel with the plurality of shape memory materials responding to the temperature of the compressed gas passed through the channel.

Assignees

• Subbareddyar Thangaraj
• Keny Mayur Abhay
• Muthuramalingam Mahendhra
• Gen Electric

Inventors

• Subbareddyar Thangaraj
• Keny Mayur Abhay
• Muthuramalingam Mahendhra

Classifications

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D25/12

  Cooling · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title