Self-regulating fuel staging port for turbine combustor
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
US-0791975
(2010-06-02)
등록번호
US-8769955
(2014-07-08)
발명자
/ 주소
Van Nieuwenhuizen, William F.
Fox, Timothy A.
Williams, Steven
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
2인용 특허 :
17
초록▼
A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting veloc
A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone (74) that acts as a valve on airflow (40, 41) through the port, in which the air outflow (41) is inversely proportion to the fuel flow (25). The fuel flow rate is controlled (65) in proportion to engine load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies (36).
대표청구항▼
1. A gas turbine engine combustor comprising a fuel staging port in a wall surrounding a combustion gas flow path, the fuel staging port comprising: a port enclosure defining an airflow path from an air opening that admits air from outside the wall to an exit hole in fluid communication with the com
1. A gas turbine engine combustor comprising a fuel staging port in a wall surrounding a combustion gas flow path, the fuel staging port comprising: a port enclosure defining an airflow path from an air opening that admits air from outside the wall to an exit hole in fluid communication with the combustion gas flow path; andfuel injectors in the port enclosure that provide a convergent fuel flow that forms a flow stagnation zone;wherein the fuel injectors are positioned to locate the flow stagnation zone such that it is effective as a valve in the airflow path, admitting an airflow through the port enclosure inversely to a rate of the convergent fuel flow. 2. The gas turbine engine combustor as in claim 1, further comprising at least three fuel injectors providing a convergent plurality of fuel streams wherein each of the fuel streams is opposed by others of the fuel streams, slowing the fuel streams and forming the stagnation zone. 3. The gas turbine engine combustor as in claim 2, wherein each of the fuel injectors is partially angled toward the exit hole in a conical convergence geometry that turns the fuel streams toward the exit hole. 4. The gas turbine engine combustor as in claim 1, wherein the wall forms a basket of a gas turbine combustor. 5. The gas turbine engine combustor as in claim 4, further comprising a compressed air plenum around the basket and a fuel control that increases the convergent fuel flow in proportion to a load of the gas turbine engine, wherein the airflow through the fuel staging port is reduced at increased engine loads, making more compressed air available via the plenum to a premixing assembly in the combustion gas flow path. 6. A gas turbine engine combustor comprising: a premixing assembly delivering a fuel/air mixture to a combustion zone;a bypass flow path effective to deliver a bypass air flow around the premixing assembly to the combustion zone; anda fuel element disposed in the bypass flow path and comprising a geometry effective to at least partially block the bypass air flow in proportion to a flow rate of fuel delivered through the fuel element. 7. The gas turbine engine combustor as in claim 6, wherein the bypass flow path comprises a port formed in a wall defining the combustion zone, the fuel element being disposed within the port. 8. The gas turbine engine combustor as in claim 7, wherein the fuel element comprises a plurality of fuel injectors providing convergent fuel flows effective to create a flow stagnation zone within the port to at least partially block the bypass air flow in proportion to the flow rate of fuel delivered through the fuel element without any moving mechanical part within the port. 9. The gas turbine engine combustor as in claim 8, comprising at least 3 fuel injectors, wherein the fuel streams are partly angled toward an exit hole in the port via a conical convergence geometry that turns each of the fuel streams toward the exit hole and into the combustion zone. 10. The gas turbine engine combustor as in claim 8, further comprising a fuel control that increases the convergent fuel flows in proportion to a load of the gas turbine engine combustor, wherein the bypass air flow through the port is reduced at increased engine loads, making more compressed air available to the premixing assembly. 11. A gas turbine engine combustor comprising a combustion zone surrounded by a wall, a compressed air plenum surrounding the wall, and characterized by: a fuel and air staging port mounted in the wall, comprising: a port enclosure that receives compressed air at a first end open to the plenum, wherein the compressed air flows through an interior path in the port enclosure and exits an exit hole to the combustion zone at a second end of the port enclosure; anda plurality of convergent fuel injectors in the port enclosure that direct respective convergent fuel streams forming a flow stagnation zone proximate the second end of the port enclosure that at least partially blocks the flow of compressed air through the port enclosure in proportion to a flow rate of the convergent fuel streams;wherein the flow rate of the convergent fuel streams inversely determines a flow rate of the compressed air through the port enclosure and the exit hole. 12. A gas turbine engine combustor as in claim 11, wherein the convergent fuel injectors provide a convergent plurality of fuel streams, and each of the fuel streams is opposed by the others of the fuel streams, thus slowing each of the fuel streams and converting a velocity pressure of each fuel stream to a static pressure, forming the stagnation zone. 13. A gas turbine engine combustor as in claim 12, wherein each of the fuel injectors is partly angled toward the exit hole in a conical convergence geometry that turns the fuel stream toward the exit hole and into the combustion gas flow path. 14. A gas turbine engine combustor as in claim 11, wherein the wall forms a basket of a gas turbine combustor. 15. A gas turbine engine combustor as in claim 14, further comprising a case around the basket forming the compressed air plenum between the case and the basket, and a fuel control mechanism outside the case that increases the convergent fuel flows in proportion to a load of the gas turbine engine, decreasing the flow of compressed air through the port enclosure.
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