Heat exchanger for cooled cooling air with adjustable damper
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/18
F28F-009/02
F02K-003/115
F02C-007/141
F04D-029/58
F28F-009/24
F28D-007/06
F28D-001/047
F28D-021/00
출원번호
US-0062400
(2016-03-07)
등록번호
US-10253695
(2019-04-09)
발명자
/ 주소
Duesler, Paul W.
Schwarz, Frederick M.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Snell & Wilmer, L.L.P.
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially w
A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.
대표청구항▼
1. A heat exchanger for cooling air in a gas turbine engine comprising: a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion;a plurality of tubes coupled to the central manifold;a shroud at least partially encasing said plurality of tubes; anda cooling
1. A heat exchanger for cooling air in a gas turbine engine comprising: a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion;a plurality of tubes coupled to the central manifold;a shroud at least partially encasing said plurality of tubes; anda cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes,the heat exchanger being coupled to the gas turbine engine via a plurality of links; andan adjustable damper coupled between the heat exchanger and the gas turbine engine, the adjustable damper comprising: a first tube,a second tube configured to be inserted at least partially into the first tube,an adjusting member;a moveable member disposed perpendicular to the second tube, the moveable member comprising a contacting surface configured to contact an outer surface of the second tube and dampen movement of the second tube by friction force;a spring member coupled between the adjusting member and the moveable member;a housing coupled to the first tube, wherein the spring member and the adjusting member are located at least partially within the housing; andan adjustable washer sandwiched between the housing and the adjusting member having a selected thickness which limits a distance the adjusting member is moved towards the housing and configured to determine the positioning of the adjusting member relative to the housing, wherein the adjustable washer is one of a plurality of adjustable washers of a varying predetermined thickness, the varying predetermined thickness being determined as a function based on a value of a changing of a spring constant of the spring member over time. 2. The heat exchanger of claim 1, wherein the adjusting member is threadingly attached to the housing, the spring member configured to compress in response to the adjusting member being turned into the housing and decompress in response to the adjusting member being turned out of the housing. 3. The heat exchanger of claim 1, wherein the first outlet portion is located on the opposite side of the inlet portion as the second outlet portion. 4. The heat exchanger of claim 1, wherein the cooling air flow path receives air from a bypass flow path of the gas turbine engine. 5. The heat exchanger of claim 1, wherein the inlet portion is configured to receive air from a high pressure compressor section of the gas turbine engine. 6. A gas turbine engine comprising: a compressor section; andan air-to-air heat exchanger in fluid communication with the compressor section, comprising: a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion;a plurality of tubes configured to receive air from the compressor section coupled to the central manifold;a shroud at least partially encasing said plurality of tubes; anda cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes,wherein, the air-to-air heat exchanger is coupled to the gas turbine engine via an adjustable damper comprising: a first tube;a second tube located at least partially within the first tube;an adjusting member;a moveable member disposed perpendicular to the second tube, the moveable member comprising a contacting surface configured to contact an outer surface of the second tube and dampen movement of the second tube by friction force; anda spring member coupled between the adjusting member and the moveable membera housing coupled to the first tube, wherein the spring member and the adjusting member are located at least partially within the housing; andan adjustable washer sandwiched between the housing and the adjusting member having a selected thickness which limits a distance the adjusting member is moved towards the housing and configured to determine the positioning of the adjusting member relative to the housing, wherein the adjustable washer is one of a plurality of adjustable washers of a varying predetermined thickness, the varying predetermined thickness being determined as a function based on a value of a changing of a spring constant of the spring member over time. 7. The gas turbine engine of claim 6, wherein a force is transferred from the first tube, through the housing, through the adjusting member, through the spring member, into the moveable member, and into the second tube. 8. The gas turbine engine of claim 7, wherein the housing is attached to the first tube, the moveable member in contact with the second tube via a cut-out in the first tube. 9. The gas turbine engine of claim 7, wherein the force is configured to dampen a movement of the second tube along a longitudinal axis. 10. The gas turbine engine of claim 9, wherein the spring member is configured to at least one of compress or decompress in response to the adjusting member moving relative to the housing. 11. The gas turbine engine of claim 6, wherein the first outlet portion is located on the opposite side of the inlet portion as the second outlet portion. 12. The gas turbine engine of claim 6, wherein the inlet portion receives air from the compressor section of the gas turbine engine and the cooling air flow path receives air from a bypass flow path of the gas turbine engine.
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이 특허에 인용된 특허 (6)
Wakeman Thomas G. (West Chester OH), Compact air-to-air heat exchanger for jet engine application.
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