[특허]Gas turbine engine dual sealing cylindrical variable bleed valve

General Electric Company

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특허 상세정보

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Gas turbine engine dual sealing cylindrical variable bleed valve

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-009/18 B64D-013/08 F01D-025/14 F02C-003/04 F02C-007/18 F02K-003/06 F01D-017/10 F02K-003/075
출원번호	US-0083392 (2016-03-29)
등록번호	US-10208676 (2019-02-19)
발명자 / 주소	Johnson, Steven Douglas Miller, Brandon Wayne Gonyou, Craig Alan
출원인 / 주소	General Electric Company
대리인 / 주소	General Electric Company
인용정보	피인용 횟수 : 0 인용 특허 : 8

초록
▼

Axially adjacent annular booster bleed aft and forward plenums with annular common wall therebetween extend radially outwardly from transition duct. Variable bleed valve includes bleed valve door in bleed inlet in transition duct, attached to rotatable valve body rotatable about axis of rotation, operable to open and close bleed inlet to aft plenum. Rotatable plenum door clocked or circumferentially spaced apart from variable bleed valve door and attached to rotatable valve body, operable to close and open up and control flow through an inter plenum aperture in common wall. Aft and forward bleed exhaust ducts extend from booster bleed aft and forward plenums to bypass flow path. One or more heat exchanger, such as from thermal management system, may be disposed in the bleed exhaust ducts. Heat exchangers may be used for cooling oil for power gear box and/or engine bearings, air conditioning, or variable frequency generator.

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1. A gas turbine engine variable bleed apparatus for use in a gas turbine engine having a centerline axis comprising: axially adjacent annular booster bleed aft and forward plenums and an annular common wall therebetween extending generally radially outwardly from a transition duct,wherein the annular booster bleed forward plenum is positioned substantially axially forward of the transition duct,a variable bleed valve including a variable bleed valve door disposed in a bleed inlet in the transition duct,the variable bleed valve door being part of or attached to a rotatable valve body pivotable or rotatable about an axis of rotation,the variable bleed valve door operable to open and close the bleed inlet to the annular booster bleed aft plenum located and extending radially outwardly from the transition duct and the bleed inlet,a rotatable plenum door clocked or circumferentially spaced apart from the variable bleed valve door and being part of or attached to the rotatable valve body, andthe rotatable plenum door operable to close and open up and control flow through an inter plenum aperture in the annular common wall between the axially adjacent annular booster bleed aft and forward plenums. 2. The gas turbine engine variable bleed apparatus as claimed in claim 1 further comprising at least one heat exchanger disposed in at least one of aft and forward bleed exhaust ducts in fluid communication with and extending from the axially adjacent annular booster bleed aft and forward plenums respectively. 3. The gas turbine engine variable bleed apparatus as claimed in claim 1 further comprising aft and forward bleed exhaust ducts in fluid communication with and extending from axially adjacent annular booster bleed aft and forward plenums respectively to a bypass flow path and at least one heat exchanger disposed in at least one of aft and forward bleed exhaust ducts. 4. The gas turbine engine variable bleed apparatus as claimed in claim 3 further comprising controlled variable or passive fixed louvers in one of the aft bleed exhaust ducts including the at least one of aft and forward bleed exhaust ducts. 5. The gas turbine engine variable bleed apparatus as claimed in claim 2 further comprising a chute on a radially outer side of the variable bleed valve door and the chute being curved and operable for directing bleed air entering the bleed inlets to and through the aft bleed exhaust duct. 6. The gas turbine engine variable bleed apparatus as claimed in claim 5 further comprising aft and forward bleed exhaust ducts in fluid communication with and extending from the axially adjacent annular booster bleed aft and forward plenums respectively to a bypass flow path and at least one heat exchanger disposed in at least one of aft and forward bleed exhaust ducts. 7. The gas turbine engine variable bleed apparatus as claimed in claim 6 further comprising controlled variable or passive fixed louvers in one of the aft bleed exhaust ducts including the at least one of aft and forward bleed exhaust ducts. 8. The gas turbine engine variable bleed apparatus as claimed in claim 2 further comprising the rotatable plenum door, the inter plenum aperture, and at least a portion of the annular common wall being cylindrical and circumscribed about the axis of rotation. 9. The gas turbine engine variable bleed apparatus as claimed in claim 8 further comprising: a chute on a radially outer side of the variable bleed valve door,the chute being curved and operable for directing bleed air entering the bleed inlets to and through the aft bleed exhaust duct,aft and forward bleed exhaust ducts in fluid communication with and extending from the axially adjacent annular booster bleed aft and forward plenums respectively to a bypass flow path and at least one heat exchanger disposed in at least one of aft and forward bleed exhaust ducts, andcontrolled variable or passive fixed louvers in one of the aft bleed exhaust ducts including the at least one of aft and forward bleed exhaust ducts. 10. An aircraft turbofan gas turbine engine comprising: an engine centerline axis,in downstream serial flow communication, a fan, a low pressure compressor or booster, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine;the high pressure turbine drivingly connected to the high pressure compressor and the low pressure turbine drivingly connected to both the fan and the low pressure compressor or the booster;a gas turbine engine variable bleed apparatus circumscribing the engine centerline axis and including axially adjacent annular booster bleed aft and forward plenums and an annular common wall therebetween extending generally radially outwardly from a transition duct between the low pressure compressor or the booster and the high pressure compressor;wherein the annular booster bleed forward plenum is positioned substantially axially forward of the transition duct,a plurality of bleed inlets in a circular row disposed through an outer annular wall of the transition duct;a variable bleed valve including a variable bleed valve door disposed in each of the bleed inlets;the variable bleed valve door being part of or attached to a rotatable valve body pivotable or rotatable about an axis of rotation;the variable bleed valve door operable to open and close the bleed inlet to the annular booster bleed aft plenum located and extending radially outwardly from the transition duct and the bleed inlet;a rotatable plenum door clocked or circumferentially spaced apart from the variable bleed valve door and being part of or attached to the rotatable valve body; andthe rotatable plenum door operable to close and open up and control flow through an inter plenum aperture in the annular common wall between the axially adjacent annular aft and forward plenums. 11. The aircraft turbofan gas turbine engine as claimed in claim 10 further comprising aft and forward bleed exhaust ducts in fluid communication with and extending from the axially adjacent annular booster bleed aft and forward plenums respectively to a bypass flow path and one or more heat exchangers disposed in one or more aft bleed exhaust ducts respectively. 12. The aircraft turbofan gas turbine engine as claimed in claim 11 further comprising a thermal management system including the one or more heat exchangers. 13. The aircraft turbofan gas turbine engine as claimed in claim 12 further comprising controlled variable or passive fixed louvers in the aft and forward bleed exhaust ducts. 14. The aircraft turbofan gas turbine engine as claimed in claim 13 further comprising a chute on a radially outer side of the variable bleed valve door and the chute being curved and operable for directing bleed air entering the bleed inlets to and through the aft bleed exhaust duct. 15. The aircraft turbofan gas turbine engine as claimed in claim 11 further comprising the rotatable plenum door, the inter plenum aperture, and at least a portion of the annular common wall being cylindrical and circumscribed about the axis of rotation. 16. The aircraft turbofan gas turbine engine as claimed in claim 15 further comprising: a chute on a radially outer side of the variable bleed valve door,the chute being curved and operable for directing bleed air entering the bleed inlets to and through the aft bleed exhaust duct,aft and forward bleed exhaust ducts in fluid communication with and extending from the axially adjacent annular booster bleed aft and forward plenums respectively to a bypass flow path,a thermal management system including one or more heat exchangers disposed in one or more aft bleed exhaust ducts respectively, andcontrolled variable or passive fixed louvers in the aft and forward bleed exhaust ducts. 17. The aircraft turbofan gas turbine engine as claimed in claim 15 further comprising: an annular fan frame circumscribed about an engine centerline axis and supporting the fan, andthe variable bleed valve door hinged by a hinge attached to a fan hub frame of the fan frame and the rotatable plenum door, the inter plenum aperture, and at least a portion of the annular common wall being cylindrical and circumscribed about the axis of rotation. 18. The aircraft turbofan gas turbine engine as claimed in claim 17 further comprising: a chute on a radially outer side of the variable bleed valve door,the chute being curved and operable for directing bleed air entering the bleed inlets to and through the aft bleed exhaust duct,the aft and forward bleed exhaust ducts in fluid communication with and extending from the axially adjacent annular booster bleed aft and forward plenums respectively to a bypass flow path,a thermal management system including one or more heat exchangers disposed in one or more of the aft bleed exhaust ducts respectively, andcontrolled variable or passive fixed louvers in the aft and forward bleed exhaust ducts. 19. The aircraft turbofan gas turbine engine as claimed in claim 17 further comprising: a fan casing circumscribing the engine centerline axis and surrounding the fan and a bypass duct containing the bypass flow path,the bypass duct located downstream or aft of the fan and spaced radially outwardly from the booster,an annular fan frame supporting the fan casing, andthe annular fan frame including an annular outer frame casing, the fan hub frame, and a plurality of circumferentially spaced apart duct struts extending between the outer frame casing and the fan hub frame. 20. The aircraft turbofan gas turbine engine as claimed in claim 19 further comprising a thermal management system including one or more heat exchangers disposed in one or more aft bleed exhaust ducts respectively. 21. The aircraft turbofan gas turbine engine as claimed in claim 20 further comprising: a power gear box operably disposed between the low pressure turbine and the fan for adjusting rotational speed of the fan relative to the low pressure turbine,engine bearings rotatably supporting at least one of the low pressure turbine, the fan, the high pressure compressor and the high pressure turbine, andone of the heat exchangers being an engine air-cooled oil cooler operable for cooling oil for the power gear box and/or engine bearings. 22. The aircraft turbofan gas turbine engine as claimed in claim 21 further comprising: second and third ones of the heat exchangers disposed in second and third ones of the aft bleed exhaust ducts respectively,the second one of the heat exchangers being an air conditioning pre-cooler heat exchanger operable for being selectively cooled using air conditioning controlled variable louvers in the second one of the aft bleed exhaust ducts, anda third one of the heat exchangers being a variable frequency generator air-cooled oil cooler for cooling oil in a variable frequency generator lubricating circuit for a variable frequency generator. 23. The aircraft turbofan gas turbine engine as claimed in claim 17 further comprising: the aircraft turbofan gas turbine engine being an unducted or open rotor aircraft turbofan gas turbine engine wherein the fan is unducted and is located forward or upstream of a circular row of unducted stator vanes, andan annular fan frame rotatably supporting the fan and an annular fan hub frame supporting an engine nacelle inwardly bounding the bypass flow path. 24. The aircraft turbofan gas turbine engine as claimed in claim 23 further comprising a thermal management system including one or more heat exchangers disposed in one or more aft bleed exhaust ducts respectively. 25. The aircraft turbofan gas turbine engine as claimed in claim 24 further comprising: a power gear box operably disposed between the low pressure turbine and the fan for adjusting rotational speed of the fan relative to the low pressure turbine,engine bearings rotatably supporting at least one of the low pressure turbine, the fan, the high pressure compressor and the high pressure turbine, andone of the heat exchangers being an engine air-cooled oil cooler operable for cooling oil for the power gear box and/or engine bearings. 26. The aircraft turbofan gas turbine engine as claimed in claim 25 further comprising: second and third ones of the heat exchangers disposed in second and third ones of the aft bleed exhaust ducts respectively,the second one of the heat exchangers being an air conditioning pre-cooler heat exchanger operable for being selectively cooled using air conditioning controlled variable louvers in the second one of the aft bleed exhaust ducts, anda third one of the heat exchangers being a variable frequency generator air-cooled oil cooler for cooling oil in a variable frequency generator lubricating circuit for a variable frequency generator.

이 특허에 인용된 특허 (8)

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Gas turbine engine dual sealing cylindrical variable bleed valve

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Gas turbine engine dual sealing cylindrical variable bleed valve

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이 특허에 인용된 특허 (8)

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