Apparatus and method for active gap monitoring for a continuous flow machine
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0997106
(2006-07-19)
|
등록번호 |
US-8708638
(2014-04-29)
|
우선권정보 |
DE-10 2005 035 540 (2005-07-29) |
국제출원번호 |
PCT/DE2006/001245
(2006-07-19)
|
§371/§102 date |
20080128
(20080128)
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국제공개번호 |
WO2007/012305
(2007-02-01)
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발명자
/ 주소 |
- Morgenstern, Stefan
- Stanka, Rudolf
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출원인 / 주소 |
|
대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
7 |
초록
▼
An apparatus and method for active gap monitoring for a continuous flow machine, in particular an aircraft propulsion device, which has a rotor and a housing which surrounds the rotor forming a rotor gap, is disclosed. The apparatus having a cooling channel which is arranged on the external circumfe
An apparatus and method for active gap monitoring for a continuous flow machine, in particular an aircraft propulsion device, which has a rotor and a housing which surrounds the rotor forming a rotor gap, is disclosed. The apparatus having a cooling channel which is arranged on the external circumference of the rotor housing and is supplied with cooling air from a plenum. The cross section of the cooling channel decreases from the plenum in the circumferential direction. This ensures homogenous cooling and reduces the weight of the apparatus.
대표청구항
▼
1. An apparatus for active gap monitoring for a continuous flow machine which has a rotor and a housing which surrounds the rotor forming a rotor gap, comprising a cooling channel, wherein the cooling channel is a structure of two deformed metal halves which are connected at a crosspiece and wherein
1. An apparatus for active gap monitoring for a continuous flow machine which has a rotor and a housing which surrounds the rotor forming a rotor gap, comprising a cooling channel, wherein the cooling channel is a structure of two deformed metal halves which are connected at a crosspiece and wherein the cooling channel structure is fastened to an external circumference of the housing, wherein the cooling channel is supplied with cooling air from a plenum, and wherein a cross section of the cooling channel decreases from the plenum in a flow direction of the cooling air through the cooling channel. 2. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein the cooling channel has a rectangular cross section. 3. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein the cooling channel has a round cross section. 4. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein a radial extension of the cross section of the cooling channel decreases in the flow direction. 5. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein an axial extension of the cross section of the cooling channel decreases in the flow direction. 6. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein several cooling channels are arranged in succession. 7. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein the cooling channel encircles only a partial circumference of the housing. 8. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein the continuous flow machine is an aircraft propulsion device. 9. The apparatus for active gap monitoring for a continuous flow machine according to claim 1, wherein the cross section of the cooling channel continuously decreases from the plenum in the flow direction. 10. A continuous flow machine, comprising: a rotor;a housing which surrounds the rotor, wherein the rotor and the housing define a rotor gap therebetween; anda cooling channel, wherein the cooling channel is a structure of two deformed metal halves which are connected at a crosspiece and wherein the cooling channel structure is fastened to an external circumference of the housing, and wherein a cross section of the cooling channel decreases from a plenum in a flow direction of cooling air through the cooling channel. 11. The continuous flow machine according to claim 10, wherein the continuous flow machine is an aircraft propulsion device. 12. The continuous flow machine according to claim 10, wherein the cooling channel defines outlet openings disposed adjacent to the housing. 13. The continuous flow machine according to claim 10, wherein a radial extension of the cross section of the cooling channel decreases in the flow direction. 14. The continuous flow machine according to claim 10, wherein an axial extension of the cross section of the cooling channel decreases in the flow direction. 15. The continuous flow machine according to claim 10, wherein the cross section of the cooling channel continuously decreases from the plenum in the flow direction. 16. A method for controlling a gap between a rotor and a housing in a gas turbine engine, comprising the steps of: flowing a cooling air through a cooling channel, wherein the cooling channel is a structure of two deformed metal halves which are connected at a crosspiece and wherein the cooling channel structure is fastened to an external circumference of the housing, and wherein a cross section of the cooling channel decreases from a plenum in a flow direction of the cooling air through the cooling channel;cooling the housing by the cooling air; andcontrolling a length of the gap by the step of cooling the housing. 17. The method according to claim 16, wherein a flow speed of the cooling air remains constant within the cooling channel. 18. The method according to claim 17, wherein the length of the gap remains substantially constant. 19. The method according to claim 16, wherein the cooling channel defines outlet openings disposed adjacent to the housing. 20. The method according to claim 16, wherein a radial extension of the cross section of the cooling channel decreases in the flow direction. 21. The method according to claim 16, wherein an axial extension of the cross section of the cooling channel decreases in the flow direction. 22. The method according to claim 16, wherein the cross section of the cooling channel continuously decreases from the plenum in the flow direction.
이 특허에 인용된 특허 (7)
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Barron Michael L. (Loveland OH) Brantley James W. (Fairfield OH) Wakeman Thomas G. (Lawrenceburg IN), Aircraft gas turbine engine backbone deflection thermal control.
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Benoist Josette,FRX ; Chaput Guillaume Henri,FRX ; Pasquiet Didier Desire Rene,FRX ; Taillant Jean-Claude Christian,FRX ; Queneherve Guy Pierre,FRX, Device for blowing gases for regulating clearances in a gas turbine engine.
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Friedel Jerome,FRX ; Lestoille Patrick Didier Michel,FRX ; Schultz Christophe,FRX ; Soupizon Jean-Luc,FRX ; Vache Jean Bernard,FRX, Device for cooling or heating a circular housing.
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Plemmons Larry W. (Fairfield OH) Proctor Robert (West Chester OH) Albers Robert J. (Park Hills KY) Gardner Donald L. (West Chester OH), Gas turbine engine case counterflow thermal control.
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Gazzillo Clement ; Croft Steven John ; Gau San-Dar ; Parent Denise Marie, Gland for transferring cooling medium to the rotor of a gas turbine.
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Glover Jeffrey (Cincinnati OH), Impingement manifold.
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Ritchie Julie A. (Cincinnati OH) Schleue Joseph H. (Cincinnati OH) Glover Jeffrey (Cincinnati OH) Tegarden Frederick W. (Glendale OH), Integral clearance control impingement manifold and environmental shield.
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