초록 ▼

A gas turbine engine has a turbine shroud and back seal plate to define a gas flow passage across turbine rotor blades. A conically shaped turbine support plate for the shroud and back seal plate has a central hub fixedly secured to a bearing mount on the inboard face of a scroll of a compressor for

A gas turbine engine has a turbine shroud and back seal plate to define a gas flow passage across turbine rotor blades. A conically shaped turbine support plate for the shroud and back seal plate has a central hub fixedly secured to a bearing mount on the inboard face of a scroll of a compressor for supplying air to a turbine combustor. The conical turbine support plate permits a first predetermined thermal excursion of the shroud and back seal plate to minimize gas leakage between the turbine blades and the turbine shroud components. A plurality of restrictor units are fixedly secured on the scroll and extend axially therefrom to locate a cap portion thereon in close spaced relationship to the turbine support plate to limit expansion of the turbine shroud components with respect to the rotor blades to prevent interference therebetween under elevated temperature conditions.

대표청구항 ▼

In a gas turbine engine of the type having a combustor and compressor with means including an inboard scroll operated at a reduced temperature and a radial turbine including a rotor having a shaft connected to the compressor and shroud components for defining a flow path across the rotor operated at

In a gas turbine engine of the type having a combustor and compressor with means including an inboard scroll operated at a reduced temperature and a radial turbine including a rotor having a shaft connected to the compressor and shroud components for defining a flow path across the rotor operated at a temperature in excess of the compressor temperature, the improvement comprising: means for supporting the shroud components including a radially inwardly located bearing support secured to the compressor scroll, an annular conically dished turbine support plate located radially outwardly of the shaft of the turbine rotor and including a peripheral surface thereon located axially of the shroud components, means for securing the shroud components to the turbine support plate, means for securing said turbine support plate to said bearing support, said trubine support plate being subjected to heat conduction from the turbine flow path to said bearing support during turbine operation to produce an axial and radial thermogradient thereacross capable of producing a relative deflectiOn between the turbine rotor and the shroud components, means forming a plurality of circumferentially spaced support surfaces on the compressor scroll at a point axially spaced from the turbine support plate, a ceramic rod extending axially outwardly of each of said support surfaces having a low coefficient of thermal expansion to maintain a control length from the compressor scroll during temperature excursion of the turbine, means on each of said ceramic rods including an axial end surface located in close spaced relationship to said turbine support plate to permit a first predetermined deflection of the turbine support plate, said end surface engaging the turbine support plate upon a predetermined deflection occurring therein to limit the movement of the turbine support plate to maintain a desired clearance between the rotor and the shroud components with the ceramic rods serving to transfer the additional loading from the turbine support plate directly to the compressor scroll.