| 摘要 |
PCT No. PCT/GB92/00017 Sec. 371 Date Oct. 1, 1993 Sec. 102(e) Date Oct. 1, 1993 PCT Filed Jan. 6, 1992 PCT Pub. No. WO92/18760 PCT Pub. Date Oct. 29, 1992.The smaller diameter end of a first stiff frustoconical casing member (74) is secured to a compressor casing (34) and the smaller diameter end of a second stiff frustoconical casing member (80) is secured to the nozzle guide vanes (40). A plurality of hollow axially extending members (86) are secured to the first and second stiff frustoconical members (74, 80) to transfer tensile and compressive stresses between the compressor casing (34) and the nozzle guide vanes (40). The larger diameter end of the first stiff frustoconical member (74) is secured to an engine casing (52) by a first radially and axially flexible member (88) to define a second chamber (100), and the larger diameter end of the second stiff frustoconical member (80) is secured to the engine casing (52) by a second radially and axially flexible member (94) to define a third chamber (102). The hollow axially extending members (86) define passages (104) to allow cooling air to flow from the first chamber (100) through the second chamber (102) to a turbine. The axially extending members (86) pass circumferentially between adjacent tubular combustion chambers (42) which have their axes arranged radially.
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