Title: Turbine support structure

Abstract: 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.

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Inventors: King, Brian P. (Greenwood, IN, US)
Smale, Charles H. (Indianapolis, IN, US)

Application Number: 627115
Filing Date: 1975-10-30
Publication_date: 1977-03-01
Assignee: General Motors Corporation (Detroit, MI)
Primary Class(es): 60/796 60/800
Other Classes:
US Patent Ref:

2622789	Dec, 1952	Lundquist	60/39.
2977758	Apr, 1961	Haworth et al.	60/39.
3037349	Jun, 1962	Gassmann	60/39.

Other Refs: 719,775

Dec, 1954	UK

Primary Examiner: Croyle, Carlton R.
Assistant Examiner: Casaregola, L. J.
Attorney: Evans; J. C.