Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaft gas turbine engine
Номер патента: GB1516460A
Опубликовано: 05-07-1978
Автор(ы):
Принадлежит: Westinghouse Electric Corp
Опубликовано: 05-07-1978
Автор(ы):
Принадлежит: Westinghouse Electric Corp
Реферат: 1516460 Gas turbine plant with separate power turbine WESTINGHOUSE ELECTRIC CORP 17 Dec 1976 [23 Dec 1975] 52761/76 Headings F1G and FIT In a gas turbine engine comprising a compressordrive turbine 12a and a power turbine 14a, the gas flow duct therebetween is defined between an outer shroud 16 and an inner shroud 18, the duct being formed by arcuate segments of the shrouds each segment being formed integrally with two stator vanes 20 each of which terminates in a concave trailing edge surface 22. An angularly-movable stator vane 24 is associated with each stator vane 20, the leading edge of the movable stator vane co-operating with the concave surface 22 of the stator vane. A circular section seal member 50 is mounted in the concave surface to co-operate with the convex leading edge of the movable vane 24 so as to provide a gas-tight seal. Each movable stator vane 24 is formed with mounting pins at its ends, the radially outer pin 36 engaging within an aperture 34 formed in the outer shroud 16, a partspherical bearing 38 being provided. A control lever 70 is mounted so as to permit angular movement of the vane. The radially inner mounting pin 44 is received within an opening 42 formed in a shroud extension piece 32 which is secured to the downstream flange 30 of the inner shroud 18 by means of bolts 146 which pass through elongate holes 144 formed in the extension piece 32 and through openings in the flange 30. The extension piece 32 may be moved in a circumferential direction by means of a member (130) carrying an eccentric pin (132) which engages within a radial slot (122) formed in the forward face of the upstream flange of the extension piece 32, such adjustment correcting mis-alignment of the pivotable vane mounting bearings. The part-spherical bearing of the inner pin 44 is shown at 48.
Intermediate transition annulus for a two shaft gas turbine engine
Номер патента: CA1062620A. Автор: David J. Amos. Владелец: Westinghouse Electric Corp. Дата публикации: 1979-09-18.