Compressor for an axial turbine engine with double contra-rotating rotors
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-001/26
F01D-005/03
F01D-015/12
F01D-025/16
F01D-025/24
F04D-019/02
F04D-029/32
F04D-029/059
F02C-003/067
출원번호
US-0918616
(2015-10-21)
등록번호
US-10260348
(2019-04-16)
우선권정보
BE-2014/0791 (2014-10-27)
발명자
/ 주소
Cracco, Cedric
출원인 / 주소
Safran Aero Boosters SA
대리인 / 주소
Sandberg Phoenix & von Gontard P.C.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
A compressor of an axial turbine engine comprising two rotors or contra-rotating drums, of which an inner rotor and an outer rotor are each provided with blade rows forming a regular alternating pattern. The inner rotor is provided with a radial annular junction fixed to the transmission shaft comin
A compressor of an axial turbine engine comprising two rotors or contra-rotating drums, of which an inner rotor and an outer rotor are each provided with blade rows forming a regular alternating pattern. The inner rotor is provided with a radial annular junction fixed to the transmission shaft coming from a turbine. The outer rotor surrounds the inner rotor. The compressor also comprises a rotating bearing linked to the outer rotor and arranged axially level with the radial junction of the inner rotor so as to align the mechanical links axially. This alignment limits the effect of centrifugal force between the clearances between the blades and the walls of the rotors. A transmission with a pinion with a radial rotation axis allows the outer rotor to be driven by the inner rotor.
대표청구항▼
1. A turbine engine, said engine comprising: a compressor and an intermediate housing mounted downstream of the compressor, said compressor comprising: an inner rotor provided with a plurality of annular blade rows and an inner radial annular junction intended to connect the inner rotor to a transmi
1. A turbine engine, said engine comprising: a compressor and an intermediate housing mounted downstream of the compressor, said compressor comprising: an inner rotor provided with a plurality of annular blade rows and an inner radial annular junction intended to connect the inner rotor to a transmission shaft of the turbine engine,an outer rotor surrounding the inner rotor and comprising a plurality of annular blade rows, wherein the blade rows of the inner and outer rotor are arranged alternately in order to compress an annular flow when the rotors turn in opposite directions;a rotating bearing linked to the outer rotor, the rotating bearing and the radial junction of the inner rotor being axially at the same position; anda transmission of movement between the rotors, configured such that the rotors rotate in opposite directions, the transmission of the movement comprising at least one pinion, the at least one pinion being mounted in rotation on an inner hub of the intermediate housing. 2. The turbine engine in accordance with claim 1, wherein the radial junction comprises a disc arranged at the same axial position as the rotating bearing. 3. The turbine engine in accordance with claim 1, wherein the rotating bearing forms a rotating link between the outer rotor and a stator of the compressor. 4. The turbine engine in accordance with claim 1, wherein the compressor comprises at least two rotating bearings linked to the outer rotor, each rotating bearing being arranged axially at the same position as a row of blades of the inner rotor. 5. The turbine engine in accordance with claim 1, wherein the compressor comprises an axis of rotation of the inner and outer rotors, the radial junction having a revolution profile about the rotation axis of the compressor, the profile extending radially, towards the inside of the inner rotor. 6. The turbine engine in accordance with claim 1, wherein the rotating bearing is arranged outside the outer rotor. 7. The turbine engine in accordance with claim 1, wherein the inner rotor includes at least one inner annular reinforcement arranged inside the inner corresponding rotor. 8. The turbine engine in accordance with claim 1, wherein the at least one pinion is an annular row of pinions, each pinion having a radially oriented rotation axis. 9. The turbine engine in accordance with claim 1, wherein the transmission comprises two ring gears each formed on one of the rotors, teeth of each ring gear extending axially towards the other ring gear. 10. The turbine engine in accordance with claim 1, wherein the transmission is placed at the level of the axial half of the outer rotor opposite the axial half of the outer rotor on which each rotating bearing mounted on the outer rotor is placed. 11. The turbine engine in accordance with claim 1, wherein the outer rotor comprises an outer circular wall linking all its blade rows and an inner shroud arranged inside the outer circular wall, the outer rotor comprises a blade row forming an axial end of the compressor linking the inner shroud to the outer circular wall. 12. The turbine engine in accordance with claim 1, wherein the inner rotor comprises an inner circular wall linking all its blade rows, the radial junction and the rotating bearing being arranged axially at the same position as the middle of the inner circular wall. 13. The turbine engine in accordance with claim 1, wherein the inner rotor comprises an inner circular wall linking all its blade rows, the outer ends of the blades of the inner rotor are free ends. 14. The turbine engine in accordance with claim 4, wherein the inner rotor comprises an inner circular wall linking all its blade rows, the outer rotor comprises an axial portion extending over less than half of its axial length, each bearing connecting the axial portion to the intermediate housing of the turbine engine being axially placed within the axial portion. 15. A compressor of an axial turbine engine, the compressor comprising: an inner rotor provided with several annular blade rows and an inner radial annular junction intended to connect the inner rotor to a transmission shaft of the axial turbine engine, andan outer rotor surrounding the inner rotor and comprising several annular blade rows; the blade rows of the inner and outer rotor being arranged alternately in order to compress an annular flow when the rotors turn in opposite directions; anda rotating bearing linked to the outer rotor, the rotating bearing and the radial junction of the inner rotor being arranged axially at the same position, wherein the inner rotor comprises an inner circular wall linking all its blade rows, and wherein the radial junction and the rotating bearing are arranged axially at the same position as the middle of the inner circular wall. 16. A turbine engine, said engine comprising: a transmission shaft;an intermediate housing comprising an inner hub; anda low pressure compressor, the low pressure compressor being mounted upstream of the intermediate housing, the low pressure compressor comprising: an inner rotor provided with several annular blade rows and an inner radial annular junction rigidly fixed to the transmission shaft of the turbine engine, the radial junction comprising an inner annular fixation interface rigidly fixed to the transmission shaft;an outer rotor surrounding the inner rotor and comprising several annular blade rows; the blade rows of the inner and outer rotor being arranged alternately in order to compress an annular flow when the rotors turn in opposite directions; anda rotating bearing linked to the outer rotor and the inner annular fixation interface of the radial junction are radially aligned one to the other; and a transmission of movement between the rotors, configured such that the rotors rotate in opposite directions, the transmission of the movement comprising at least one pinion, the at least one pinion being mounted in rotation on the inner hub. 17. The turbine engine in accordance with claim 16, wherein the intermediate housing comprises an intermediate body and an annular supporting body extending axially upstream from the intermediate body, the rotating bearing being mounted inside the annular supporting body.
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이 특허에 인용된 특허 (3)
Gruner George P. (13 Bradley Rd. Andover MA 01810), Contra-rotating rotors with differential gearing.
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