Power generation system exhaust cooling

Patent metadata

Field	Value
Publication number	US-10030558-B2
Application number	US-201514753077-A
Country	US
Kind code	B2
Filing date	Jun 29, 2015
Priority date	Jun 29, 2015
Publication date	Jul 24, 2018
Grant date	Jul 24, 2018

Abstract

An airflow system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

First claim

What is claimed is:

1. An airflow control system for a gas turbine system, comprising:
a compressor component of the gas turbine system, the compressor component including a first set of compressor stages for generating a first excess flow of air and a second set of compressor stages, the gas turbine system further including a combustor component and a turbine component;
an airflow generation system for attachment to a rotatable shaft of the gas turbine system upstream of the compressor component, the airflow generation system drawing in a second excess flow of air;
a mixing area for receiving an exhaust gas stream from the turbine component of the gas turbine system;
an air extraction system for extracting at least a portion of the first excess flow of air generated by the first set of compressor stages of the compressor component, and for extracting at least a portion of the second excess flow of air generated by the airflow generation system, to provide bypass air, and for diverting the bypass air through a bypass duct completely around the combustor component and the turbine component of the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream;
wherein the air extraction system includes a duct system for providing bypass air, the duct system including an a first extraction duct, a second extraction duct, and the bypass duct, wherein the first extraction duct extracts at least a portion of the first excess flow of air generated by the first set of compressor stages to provide a first portion of the bypass air, and diverts the first portion of the bypass air into the bypass duct, and wherein the second extraction duct extracts at least a portion of the second excess flow of air generated by the airflow generation system to provide a second portion of the bypass air, and diverts the second portion of the bypass air into the bypass duct;
a flow restriction system for selectively restricting airflow through at least one of the first and second extraction ducts, the flow restriction system including an actively controlled damper assembly for regulating the airflow through the at least one of the first and second extraction ducts into the bypass duct; and
an actively controlled air release system upstream from the mixing area for selectively releasing a portion of the bypass air from the bypass duct to an exterior of the turbine system to control the temperature of the exhaust.

2. The airflow control system of claim 1 , wherein the first and second excess flow of air generated by the airflow generation system and the compressor component is 10% to 40% greater than a flow rate capacity of at least one of the combustor component and the component of the gas turbine system.

3. The airflow control system of claim 1 , wherein the compressor component of the gas turbine system has an airflow output greater than a flow rate capacity of the combustor component.

4. The airflow control system of claim 1 , wherein the airflow generation system comprises a fan.

5. The airflow control system of claim 1 , wherein the air extraction system is configured to divert a portion of the second excess flow of air into the compressor component.

6. The airflow control system of claim 1 , further comprising a selective catalytic reduction (SCR) system for processing the reduced temperature exhaust gas stream.

7. A turbomachine system, comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, wherein the compressor component of the gas turbine system has an airflow output greater than a flow rate capacity of the combustor component, the compressor component including a first set of compressor stages for generating a first excess flow of air and a second set of compressor stages;
a shaft driven by the turbine component;
a fan coupled to the shaft upstream of the compressor component of the gas turbine system, the fan and the compressor component drawing in a second excess flow of air;
a mixing area for receiving an exhaust gas stream from the turbine component of the gas turbine system;
an air extraction system for: extracting at least a portion of the second excess flow of air generated by the fan and for extracting at least a portion of the first excess flow of air generated by the first set of compressor stages of the compressor component to provide bypass air; and diverting the bypass air through a bypass duct completely around the combustor component and the turbine component of the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream;
an exhaust processing system for processing the reduced temperature exhaust gas stream;
wherein the air extraction system includes a duct system for providing bypass air, the duct system including a first extraction duct, a second extraction duct, and the bypass duct, wherein the first extraction duct extracts at least a portion of the first excess flow of air generated by the first set of compressor stages to provide a first portion of the bypass air, and diverts the first portion of the bypass air into the bypass duct, and wherein the second extraction duct extracts at least a portion of the second excess flow of air generated by the airflow generation system to provide a second portion of the bypass air, and diverts the second portion of the bypass air into the bypass duct;
a flow restriction system for selectively restricting airflow through at least one of the first and second extraction duct, the flow restriction system including an actively controlled damper assembly for regulating the airflow through the at least one of the first and second extraction duct into the bypass duct;

and
an actively controlled air release system upstream from the mixing area for selectively releasing a portion of the bypass air from the bypass duct to an exterior of the turbine system to control the temperature of the exhaust.

8. The turbomachine system of claim 7 , wherein the first and second excess flow of air generated by the fan and the compressor component is 10% 40% greater than a flow rate capacity of at least one of the combustor component and the turbine component of the gas turbine system.

9. The turbomachine system of claim 7 , wherein the air extraction system is configured to divert a portion of the second excess flow of air into the compressor component.

10. The turbomachine system of claim 7 , wherein the exhaust processing system comprises a selective catalytic reduction (SCR) system.

Assignees

• Gen Electric

Inventors

• Reed Robert Joseph
• Davis Jr Lewis Berkley
• Kulkarni Parag Prakash

Classifications

• F05D2270/082

  with as little NOx as possible · CPC title

• F02C6/08

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

• F01N3/2066

  Selective catalytic reduction [SCR] · CPC title

• F01N2610/14

  Arrangements for the supply of substances, e.g. conduits · CPC title

• F01N2570/14

  Nitrogen oxides · CPC title