IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0133286
(2002-04-26)
|
발명자
/ 주소 |
- Jasklowski, Christophe
- Carrier, Gilles
- Thibeault, Robert
|
출원인 / 주소 |
- Pratt & Whitney Canada Corp.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
40 인용 특허 :
8 |
초록
▼
A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about ra
A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about radially extending blades of a turbine rotor and partially defines an annular hot gas passage of the turbine portion. The plurality of arcuate shroud support segments are radially disposed outwardly of the ceramic shroud ring and are contiguous therewith. The plurality of inwardly biased resilient members are each engaged between one of the shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than the ceramic shroud ring. The resilient members maintain contact between the shroud support segments and the ceramic shroud ring. The shroud supporting segments and the resilient members are adapted to deflect to compensate for relative thermal growth differences between the ceramic shroud ring and the turbine support case.
대표청구항
▼
A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about ra
A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about radially extending blades of a turbine rotor and partially defines an annular hot gas passage of the turbine portion. The plurality of arcuate shroud support segments are radially disposed outwardly of the ceramic shroud ring and are contiguous therewith. The plurality of inwardly biased resilient members are each engaged between one of the shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than the ceramic shroud ring. The resilient members maintain contact between the shroud support segments and the ceramic shroud ring. The shroud supporting segments and the resilient members are adapted to deflect to compensate for relative thermal growth differences between the ceramic shroud ring and the turbine support case. 00, Huber; US-5465808, 19951100, Musgrove; US-5507496, 19960400, Yeung; US-5551831, 19960900, Corbett; US-5556250, 19960900, Fretwell et al.; US-5564884, 19961000, Farsai; US-5575438, 19961100, McGonigle et al.; US-5677506, 19971000, Wallin; US-5758785, 19980600, Spinosa et al.; US-5816552, 19981000, Chapman, 248/281.11; US-5907111, 19990500, Josten et al., 073/866.5; US-5949015, 19990900, Smith et al.; US-6009791, 20000100, Medlin; US-6098823, 20000800, Yahiaoui; US-6113343, 20000900, Goldenberg et al.; US-6158555, 20001200, Brown, Jr.; US-6174124, 20010100, Haverfield et al.; US-6260310, 20010700, Price et al.; US-6302010, 20011000, Holler
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