Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-009/06
F01D-009/00
F01D-005/18
출원번호
UP-0236524
(2005-09-28)
등록번호
US-7581920
(2009-09-16)
우선권정보
FR-04 52202(2004-09-30)
발명자
/ 주소
Lardellier, Alain
출원인 / 주소
SNECMA
대리인 / 주소
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
인용정보
피인용 횟수 :
2인용 특허 :
3
초록▼
An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades, and sucking in air from the minimized inner flowpath through a radially inner orifice of a vane faced b
An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades, and sucking in air from the minimized inner flowpath through a radially inner orifice of a vane faced by the labyrinths. The method further includes directing the sucked in air through the vane, bleeding the air from the vane through a radially outer opening of the vane and through an orifice of an outer casing. The air is collected from the vane into a manifold outside the compression stage. A compressor arrangement for circulating air includes a suction device for sucking in air present in the inner flowpath between labyrinths and the vane, and for sending the air into the vane of the stator. The arrangement also includes a device for bleeding air in the vane of the stator and for sending the air outside the compressor.
대표청구항▼
The invention claimed is: 1. An air circulation method in a turbomachine compressor, said compressor comprising: several compression stages each composed of a bladed rotor with blades and a bladed stator with vanes, an outer casing and an inner casing, delimiting a flowpath in which the blades of t
The invention claimed is: 1. An air circulation method in a turbomachine compressor, said compressor comprising: several compression stages each composed of a bladed rotor with blades and a bladed stator with vanes, an outer casing and an inner casing, delimiting a flowpath in which the blades of the rotor and the vanes of the stator are located, a main airflow passing through said flowpath, an outer part of the flowpath called the outer flowpath, corresponding to functional clearances between the outer casing and the blades of the rotor, and an inner part of the flowpath called the inner flowpath, corresponding to functional clearances between the inner casing and the vanes of the stator, the method comprising the following steps, for at least one compression stage comprising a stator: providing labyrinths on said inner casing between said two adjacent blades, said labyrinths facing a vane between said two adjacent blades, wherein said labyrinths do not touch said vane such that said functional clearances defining said inner flowpath are present between said labyrinths and said vane, sucking in air from the main airflow, through said functional clearances between said labyrinths and said vane and through a radially inner orifice of said vane faced by said labyrinths, directing the sucked in air through said vane, bleeding said air from said vane through a radially outer opening of said vane and through an orifice of said outer casing, and collecting said air from said vane into a manifold outside the compression stage. 2. An air circulation method according to claim 1, further comprising sucking air into at least one blade of at least one rotor adjacent to said stator, and sending said air into at least one vane of said at least one stator. 3. An air circulation method according to claim 2, further comprising sucking air into the outer flowpath and sending said air into the at least one blade of at least one rotor. 4. An air circulation method according to claim 2, further comprising sucking air in at a suction face of a profile of said at least one blade of said at least one rotor, and sending said air into said at least one blade of said at least one rotor, and sucking in said air at the suction face of the profile of said at least one vane of said stator, and sending said air into said at least one vane of said stator. 5. An air circulation method according to claim 3, further comprising sucking air in at a suction face of a profile of said at least one blade of said at least one rotor, and sending said air into said at least one blade of said at least one rotor, and sucking said air in at the suction face of the profile of said at least one vane of said stator, and sending said air into at least one vane of said stator. 6. An air circulation method according to claim 2, comprising sucking air into at least one blade of the rotor located on an upstream side of said stator and adjacent to said stator, and sending said air into at least one vane of said stator. 7. An air circulation method according to claim 2, comprising sucking air into at least one blade of the rotor located on a downstream side of said stator and adjacent to said stator, and sending said air into at least one vane of said stator. 8. An air circulation method according to claim 2, comprising sucking air into at least one blade in each of the two rotors located on each side of said stator, and sending said air into at least one vane of said stator. 9. An air circulation method according to claim 1, further comprising sucking air and sending said air into an intermediate chamber, and bleeding said air from said intermediate chamber inside the compressor. 10. An air circulation method according to claim 9, comprising sucking air into at least one blade of at least one rotor adjacent to said stator, and sending said air into said intermediate chamber. 11. An air circulation method according to claim 10, comprising sucking air into the outer flowpath and sending the air into said at least one blade of said at least one rotor. 12. An air circulation method according to claim 10, comprising sucking air in at a suction face of a profile of said at least one blade of said at least one rotor, and sending the air into said at least one blade of said at least one rotor, and sucking air in at the suction face of the profile of said at least one vane of said at least one stator, and sending the air into said at least one vane of said stator. 13. An air circulation method according to claim 10, comprising sucking air into at least one blade of the rotor located on an upstream side of said stator and adjacent to the stator, and sending the air into said intermediate chamber. 14. An air circulation method according to claim 10, comprising sucking air into at least one blade in each of the two rotors located on each side of said stator, and sending the air into said intermediate chamber. 15. A compressor arrangement for circulating air, said compressor arrangement comprising: several compression stages each composed of a bladed rotor with blades and a bladed stator with vanes, an outer casing and an inner casing, delimiting a flowpath in which the blades of each rotor and the vanes of each stator are located, a main airflow passing through said flowpath, an outer part of the flowpath called the outer flowpath, corresponding to functional clearances between the outer casing and the blades of each rotor, and an inner part of the flowpath called the inner flowpath, corresponding to functional clearances between the inner casing and the vanes of each stator, the compressor arrangement further comprising, for at least one compression stage comprising a stator: labyrinths on said inner casing between two adjacent blades, said labyrinths facing a vane between said two adjacent blades, wherein said labyrinths do not touch said vane such that said functional clearances defining said inner flowpath are present between said labyrinths and said vane, first suction means for sucking in air from the main airflow, through said functional clearances between said labyrinths and the vane, and for sending said air into said vane of said stator, and bleed means for bleeding air in said vane of said stator and for sending said air outside the compressor. 16. A compressor arrangement according to claim 15, further comprising: second suction means for sucking air into at least one blade of at least one rotor adjacent to said stator, and for sending said air into at least one vane of said stator. 17. A compressor arrangement according to claim 16, further comprising: third suction means for sucking air into the outer flowpath, and for sending said air into at least one blade of said at least one rotor. 18. A compressor arrangement according to claim 16 further comprising: fourth suction means for sucking air in at a suction face of a profile of at least one vane of said stator, and for sending said air into said at least one vane of said stator, and fifth suction means for sucking air in at the suction face of the profile of at least one blade of said at least one rotor, and for sending said air directly into said at least one blade of said at least one rotor. 19. A compressor arrangement according to claim 17, further comprising: fourth suction means for sucking air in at a suction face of a profile of at least one vane of said stator, and for sending said air into said at least one vane of said stator, and fifth suction means for sucking air in at the suction face of the profile of at least one blade of said at least one rotor, and for sending said air directly into said at least one blade of said at least one rotor. 20. A compressor arrangement according to claim 16, further comprising: second suction means for sucking air into at least one blade of the rotor located on the upstream side of said stator, and for sending said air into at least one vane of said stator. 21. A compressor arrangement according to claim 16, further comprising: second suction means for sucking air into at least one blade of the rotor located on the downstream side of said stator, and for sending said air into at least one vane of said stator. 22. A compressor arrangement according to claim 16, further comprising: second suction means for sucking air into at least one blade in each of the two rotors located on each side of said stator, and for sending said air into at least one vane of said stator. 23. A compressor arrangement according to claim 15, wherein said first suction means comprise an inner cavity in said vane opening up into the inner flowpath through an orifice. 24. A compressor arrangement according to claim 16, wherein said second suction means comprise: an inner cavity in said blade, that opens up in an orifice on the upstream side or the downstream side of said rotor in an inner chamber delimited by the inner casing, and at least one through opening in the inner casing that creates a communication between said inner chamber and the inner flowpath at least one location facing a vane of said stator. 25. A compressor arrangement according to claim 17, wherein said third suction means comprise an inner cavity in said blade, that opens up in an orifice in the outer flowpath. 26. A compressor arrangement according to claim 18, wherein: said fourth suction means comprise an inner cavity in said vane and at least one lateral through orifice that creates a communication between the suction face of said vane and its inner cavity, and said fifth suction means comprise an inner cavity in said blade and at least one lateral through orifice that creates communication between the suction face of said blade and its inner cavity. 27. A compressor arrangement according to claim 19, wherein: said first suction means comprise an inner cavity in said vane opening up in the inner flowpath through an orifice, said second suction means comprise: an inner cavity in said blade that opens up in an orifice on an upstream side or a downstream side of said rotor in an inner chamber delimited by the inner casing, and at least one through opening in the inner casing that creates a communication between said inner chamber and the inner flowpath at least one location facing a vane of said stator, said third suction means comprise an inner cavity in said blade, that opens up in an orifice in the outer flowpath, said fourth suction means comprise an inner cavity in said vane and at least one lateral through orifice that creates a communication between the suction face of said vane and its inner cavity, and said fifth suction means comprise an inner cavity in said blade and at least one lateral through orifice that creates a communication between a suction face of said blade and its inner cavity. 28. A compressor arrangement according to claim 15, wherein said bleed means comprise a through opening that creates a communication between an inner cavity of said vane and the outside of the flowpath. 29. A compressor arrangement according to claim 27, wherein said bleed means comprise a through opening that creates communication between an inner cavity of said vane and the outside of the flowpath. 30. A compressor arrangement according to claim 29, wherein said bleed means also comprise at least one manifold in which said through opening opens up. 31. A compressor arrangement according to claim 15, further comprising an intermediate shell located between the inner casing and the outer casing, that connects the blades to each other, and that delimits an intermediate chamber with the blades and with said inner casing. 32. A compressor arrangement according to claim 27, further comprising an intermediate shell located between the inner casing and the outer casing, that connects the blades to each other, and that delimits an intermediate chamber with the blades and with said inner casing. 33. A compressor arrangement according to claim 32, further comprising additional suction means, that create a communication between said intermediate chamber and the inner chamber. 34. A compressor arrangement according to claim 33, wherein said additional suction means comprise at least one suction duct defined between the connecting flanges of the shells assembled to each other to form the inner casing. 35. An air compression stage of a turbomachine, wherein said air compression stage comprises a compressor arrangement according to claim 15. 36. An air compression stage of a turbomachine, wherein said air compression stage comprises a compressor arrangement according to claim 27. 37. An aircraft engine equipped with a compressor comprising at least one compressor arrangement according to claim 15. 38. An aircraft engine equipped with a compressor comprising at least one compressor arrangement according to claim 27.
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