Compressor in a multi-stage axial form of construction
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0423744
(2003-04-25)
|
우선권정보 |
DE-102 18 459(2002-04-25) |
발명자
/ 주소 |
- Albrecht,Guenter
- Tartsch,Klaus Dieter
- Tomsik,Joseph
- Woehrl,Bernhard
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
7 |
초록
▼
A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stage forms the blade cascade arranged
A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stage forms the blade cascade arranged furthest upstream. At least one of the rotating blade carriers is produced in an MMC form of construction, that is to say as a metal component fiber-reinforced at least in regions, and the rotary bearing absorbing the large part of the radial loads occurring on the rotor has a predetermined breaking point which, when a defined radial load is exceeded, allows a radial shift of the rotor, with the result that the latter brushes against the stator.
대표청구항
▼
What is claimed is: 1. A compressor in a multi-stage axial form of construction with a high fluidic efficiency, comprising: a rotor mounted overhung and including a plurality of moving-blade rings on at least one of disc-shaped and annular blade carriers connected to one another, at least one blade
What is claimed is: 1. A compressor in a multi-stage axial form of construction with a high fluidic efficiency, comprising: a rotor mounted overhung and including a plurality of moving-blade rings on at least one of disc-shaped and annular blade carriers connected to one another, at least one blade carrier produced in a metal matrix composite form of construction; a blade arrangement without a pre-guide cascade, a moving-blade ring of a first compressor stage forming a blade cascade arranged furthest upstream; and a rotary bearing arranged to absorb at least a majority of radial loads occurring on the rotor and including a predetermined breaking point configured to allow a limited radial shift of the rotor when a defined radial load is exceeded so that the rotor brushes against a stator of the compressor to reduce a rotational speed potentially to a standstill. 2. The compressor according to claim 1, wherein the compressor is arranged as a low-pressure compressor of an aircraft gas turbine. 3. The compressor according to claim 1, wherein the rotor is connected to a shaft end projecting from the rotary bearing. 4. The compressor according to claim 1, wherein the at least one blade carrier is produced as a metal component fiber-reinforced at least in regions. 5. The compressor according to claim 4, wherein the at least one blade carrier includes, in the fiber-reinforced region, a metallic matrix and at least one long fiber arranged in windings and including silicon carbide. 6. The compressor according to claim 5, wherein the metal matrix is arranged on a titanium base. 7. The compressor according to claim 1, wherein the at least one blade carrier is arranged as an annular component as a bling including a materially-integrated fiber-reinforced region. 8. The compressor according to claim 7, wherein the at least one blade carrier includes integral blading. 9. The compressor according to claim 1, wherein the at least one blade carrier is arranged as a disc-shaped component including two fiber-reinforced regions arranged symmetrically to an axial disc center, the two fiber-reinforced regions one of materially integrated and frictionally and positively fastened. 10. The compressor according to claim 9, wherein the disc-shaped component includes integral blading. 11. The compressor according to claim 9, wherein the disc-shaped component is arranged as a blisk. 12. The compressor according to claim 1, wherein the predetermined breaking point at the rotary bearing includes ball guides arranged to deflect radial loads, with reinforcement, into axial forces and tension bolts arranged to break when a defined axial force is exceeded. 13. The compressor according to claim 1, wherein the predetermined breaking point at the rotary bearing includes shearing rings arranged to break when a defined radial load is exceeded. 14. The compressor according to claim 1, wherein the rotary bearing includes a rolling bearing in a radial form of construction. 15. The compressor according to claim 1, wherein the rotary bearing includes a cylindrical roller bearing. 16. The compressor according to claim 1, wherein the rotary bearing is arranged on a frustoconical carrier that widens in a downstream direction and is connected downstream of the rotor to a stator of the compressor. 17. The compressor according to claim 1, wherein the rotary bearing includes a brush seal on at least one side. 18. The compressor according to claim 1, wherein at least one moving-blade ring of the rotor is combined fluidically with a casing treatment. 19. The compressor according to claim 1, wherein at least one moving-blade ring includes a plurality of casing-side recirculation ducts in a blade-tip region.
이 특허에 인용된 특허 (7)
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Diepolder Wolfgang,DEX ; Woehrl Bernhard,DEX, Bearing arrangement for rotating members.
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Hyde Philip M. (Sherborne GB2) Cave Andrew M. (Yeovil GB2), Bearing assemblies for rotating shafts.
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Freeman Christopher,GBX ; Farrar Peter G G,GBX ; Richards Martyn,GBX ; Allen John W,GBX ; Udall Kenneth F,GBX ; Beaven David M,GBX, Ducted fan gas turbine engine having a frangible connection.
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Vondrell Randy M. ; Tseng Wu-Yang ; Glynn Christopher C., Fan decoupler system for a gas turbine engine.
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Van Duyn Keven G., Method and apparatus for supporting a rotatable shaft within a gas turbine engine.
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Wei William (Munich DEX) Krger Wolfgang (Reichertshausen DEX), Method for manufacturing fiber-reinforced components for propulsion plants.
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Koff Steven G. (Cambridge MA) Nikkanen John P. (West Hartford CT) Mazzawy Robert S. (South Glastonbury CT), Rotor case treatment.
이 특허를 인용한 특허 (9)
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Burghardt, Sascha, Aircraft engine.
-
Behaghel, Laurent Donatien; Gille, Laurent; Pegouet, Benjamin Philippe Pierre, Centripetal air bleed from a turbomachine compressor rotor.
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Higashio, Atsushi; Matsubayashi, Kazumi, Compressor and method of assembling the same.
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Reynolds, Bruce David; Nolcheff, Nick, Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof.
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Schreiber, Karl, Intake cone in a fiber compound material for a gas turbine engine and method for its manufacture.
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Malmborg, Eric W.; Bintz, Matthew E., Rotor assembly for gas turbine engine.
-
Plona,Daniel, Rotor recentering after decoupling.
-
Gillespie, Christopher, Thrust bearing housing for a gas turbine engine.
-
Lefebvre, Guy; Durocher, Eric, Turbine section architecture for gas turbine engine.
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