Inlet bleed heat system thermal lag mitigation using compressor interstage bleeds
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0353543
(2009-01-14)
|
등록번호 |
US-8220275
(2012-07-17)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
7 |
초록
▼
A system to mitigate thermal lag of start-up operations of a gas turbine is provided and includes a housing which is disposed upstream from and which is fluidly coupled to a compressor of the gas turbine, a first system coupled to an aft portion of the compressor and to the housing which, when activ
A system to mitigate thermal lag of start-up operations of a gas turbine is provided and includes a housing which is disposed upstream from and which is fluidly coupled to a compressor of the gas turbine, a first system coupled to an aft portion of the compressor and to the housing which, when activated, receives a first air supply from the compressor and delivers the first air supply to the housing, and a second system, coupled to the first system, which removes a second air supply from an intermediate portion of the compressor and delivers the second air supply to the first system prior to the activation of the first system.
대표청구항
▼
1. A system to mitigate thermal lag of start-up operations of a gas turbine, the system comprising: a housing which is disposed upstream from and which is fluidly coupled to a compressor of the gas turbine;a first system coupled at a first end thereof to an extraction point at an aft portion of the
1. A system to mitigate thermal lag of start-up operations of a gas turbine, the system comprising: a housing which is disposed upstream from and which is fluidly coupled to a compressor of the gas turbine;a first system coupled at a first end thereof to an extraction point at an aft portion of the compressor and at a second end thereof to the housing which is configured to receive, when activated, a first air supply from the compressor and to deliver the first air supply to the housing; anda second system, coupled to the first system proximate to the first end of the first system at an axial location of the extraction point, which is configured to removes a second air supply from an intermediate portion of the compressor and to deliver the second air supply to the first system at the axial location of the extraction point prior to the activation of the first system. 2. The system according to claim 1, wherein the housing comprises a filter housing including an inlet to which the first system is coupled and an outlet by which the filter housing fluidly communicates with the compressor. 3. The system according to claim 1, wherein the first system comprises piping warmed by the second air supply prior to the activation of the first system. 4. The system according to claim 1, wherein the first system comprises an inlet bleed heat (IBH) system. 5. The system according to claim 1, wherein the second system removes the second air supply from multiple axial locations of an intermediate portion of the compressor, the intermediate portion being located forward from an aft portion. 6. The system according to claim 1, wherein the second system comprises an interstage bleed system. 7. The system according to claim 6, wherein the interstage bleed system removes the second air supply from the intermediate portion of the compressor to regulate a compressor load. 8. The system according to claim 1, wherein the second air supply is delivered to the housing via the first system. 9. The system according to claim 1, wherein the second air supply is vented to atmosphere surrounding the gas turbine via the first system. 10. The system according to claim 1, wherein the first system comprises: a radially oriented extraction component, which extends substantially along a radial dimension from the first end of the first system;an axially oriented delivery component, which is disposed downstream from the radially oriented extraction component, which extends substantially along an axial dimension transverse to the radial dimension, and which terminates with the second end of the first system; anda connection by which the extraction component and the delivery component are fluidly coupled with one another. 11. The system according to claim 10, wherein the second system delivers the second air supply to the first system along the radially oriented extraction component. 12. A system to mitigate thermal lag of start-up operations of a gas turbine, including a compressor and a housing disposed upstream from and fluidly coupled to the compressor, the system comprising: an inlet bleed heat (IBH) system coupled to an extraction point at an aft portion of the compressor at a first end thereof and to the housing at a second end thereof which is configured to receive, when activated, a first air supply from the compressor and to deliver the first air supply to the housing; andan interstage bleed system, coupled to the IBH system proximate to the first end thereof at an axial location of the extraction point, which is configured to remove a second air supply from an intermediate portion of the compressor, which is forward from the aft portion thereof, and to deliver the second air supply to the IBH system proximate to the axial location of the extraction point prior to the activation of the IBH system. 13. A method of mitigating thermal lag of start-up operations of a gas turbine, including a compressor and a housing disposed upstream from and fluidly coupled to the compressor, the method comprising: initiating an operation of the compressor;removing warming air from an intermediate portion of the compressor;delivering the warming air to an inlet bleed heat (IBH) system proximate to a first end thereof, the IBH system being coupled to an aft portion of the compressor at the first end thereof and to the housing at a second end thereof; andactivating the IBH system to receive a hot air supply from an extraction point at the aft end of the compressor and to deliver the hot air supply to the housing,the delivering of the warming air to the IBH system being conducted at an axial location of the extraction point and prior to the activating. 14. The method according to claim 13, further comprising delivering the warming air to the housing. 15. The method according to claim 13, further comprising venting the warming air to an atmosphere surrounding the gas turbine.
이 특허에 인용된 특허 (7)
-
Anderson Rodger O. (Scotia NY) Burrow Julian D. (Ballston Lake NY) Vandervort Christian L. (Voorheesville NY), Gas turbine inlet heating system using jet blower.
-
Seki Naoyuki,JPX ; Arimura Hisato,JPX, Gas turbine starting method.
-
Motoaki Utamura JP, Gas turbine, combined cycle plant and compressor.
-
Arar Malath Ibrahim ; Kemp Timothy Robert ; Hubschmitt George Raymond ; DeAngelis David Anthony ; Eignor James Giles, High pressure inlet bleed heat system for the compressor of a turbine.
-
Briesch Michael S. (Orlando FL), Method and apparatus for warming a steam turbine in a combined cycle power plant.
-
Baer,Joan Mae; Laster,Walter Ray; Keller,Douglas Allen, Method for operating a gas turbine.
-
Turco,John B.; Wollenweber,Gary Craig, Methods and apparatus for operating gas turbine engines.
이 특허를 인용한 특허 (1)
-
Ballard, Jr., Henry G.; Beadie, Douglas Frank; Memmer, John David, Method and apparatus for clearance control utilizing fuel heating.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.