Cooling for the retaining dovetail of a turbomachine blade
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F03D-001/06
F01D-005/08
출원번호
US-0349484
(2012-10-10)
등록번호
US-9631495
(2017-04-25)
우선권정보
FR-11 59131 (2011-10-10)
국제출원번호
PCT/FR2012/052304
(2012-10-10)
국제공개번호
WO2013/054043
(2013-04-18)
발명자
/ 주소
Da Costa, Emmanuel
Gendraud, Alain Dominique
Martet, Renaud
Sicard, Josselin
Varin, Bruno Andre Jean
출원인 / 주소
SNECMA
대리인 / 주소
Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보
피인용 횟수 :
0인용 특허 :
27
초록▼
A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc incl
A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.
대표청구항▼
1. A turbine engine assembly, comprising: a disc including a set of bulbs and recesses;a blade including a bulb and a set of recesses, the bulbs of the disc configured to cooperate with the recesses of the blade, one of the recesses of the disc configured to cooperate with the bulb of the blade, the
1. A turbine engine assembly, comprising: a disc including a set of bulbs and recesses;a blade including a bulb and a set of recesses, the bulbs of the disc configured to cooperate with the recesses of the blade, one of the recesses of the disc configured to cooperate with the bulb of the blade, the bulb of the blade being arranged relative to the one of the recesses of the disc to form therebetween, when the bulb cooperates with the one of the recesses of the disc, a main channel through which a main cooling air flow can pass; anda foil configured to be positioned at least partly between the disc and the blade,wherein the foil is configured to cover mainly one of the bulbs of the disc and to be held, radially relative to the disc, by the bulb of the disc and the recess of the blade configured to cooperate therewith, when the bulb of the disc and the recess of the blade are actually cooperating,wherein the bulb of the disc includes at least one longitudinal cavity configured to form, together with the foil, when the foil is covering the bulb of the disc, a secondary channel through which a secondary cooling air flow can pass, andwherein the bulb of the disc is configured to be covered by a portion of the foil being circumferentially positioned between two recesses of the disc, the foil includes, on one side, a long end configured to cover at least partly one of the two recesses of the disc and, on an other side, a short end. 2. An assembly according to claim 1, wherein the long end of the foil is extended by portions which bear against walls of the disc for axially locking the foil with respect to the recess covered by the long end. 3. An assembly according to claim 1, wherein the bulb of the disc includes at least two longitudinal cavities separated by an apex of the bulb, the cavities configured, when the foil is covering the bulb, to form two secondary channels through which two secondary cooling air flows can pass. 4. An assembly according to claim 1, further comprising a sealing lock ring joining the disc and the blade upstream of the blade in a direction in which the main and secondary cooling air flows pass, the sealing lock ring including a set of radial cavities via which the secondary cooling air flow can be routed into the secondary channel. 5. An assembly according to claim 4, wherein the sealing lock ring further includes a set of radial grooves through which the blade can pass when the sealing lock ring joins the disc and the blade, the assembly further comprising: a movable ring including a set of radial projections configured to be housed in the radial grooves of the sealing lock ring to prevent any rotation of the sealing lock ring. 6. An assembly according to claim 5, wherein the movable ring is arranged to cause axial stopping of the blade upstream, in a direction in which the main and secondary cooling air flows pass. 7. An assembly according to claim 5, further comprising a plurality of blades, wherein the sealing lock ring includes radial grooves and the movable ring includes radial projections, a number of the radial grooves and the radial projections being the same as a number of hooks of blades configured to cooperate with the disc, and the movable ring is arranged to cause axial stopping of the blades upstream, in a direction in which the main and secondary cooling air flows pass.
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이 특허에 인용된 특허 (27)
Kulesa Joseph C. (West Chester OH) Crawford ; Jr. David E. (Cincinnati OH), Apparatus for retaining rotor blades.
Garin, Fabrice Marcel Noel; Gendraud, Alain Dominique; Lequitte, Thierry; Lunel, Romain Nicolas, Interface element between a blade root and a blade root housing of a turbine disc, and turbine rotor comprising an interface element.
Derclaye, Alain; Ernst, Philippe, Platform and blade for a bladed wheel of a turbomachine, bladed wheel and compressor or turbomachine comprising such a bladed wheel.
Belmonte, Olivier; Goga, Jean-Luc Christian Yvon; Mahieu, Jean-Noël, Spacer interposed between a blade root and the bottom of a slot in the disk in which the blade is mounted.
Serge Louis Antunes FR; Eric Stephan Bil FR; Isabelle Monique Marie Bourriaud FR; Maurice Guy Judet FR, System for ventilating a pair of juxtaposed vane platforms.
Herzner Fredrick C. (Fairfield OH) Juenger Jerome A. (Cincinnati OH) Wayte Peter (Cincinnati OH), Turbine blade wear protection system with multilayer shim.
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