Patent References 3620012 3775975 3861139 3908361 Integral infrared radiation suppressor for a turbofan engine Rotary pressure seal structure and method for reducing thermal stresses therein Casing structure for a gas turbine engine Patent #: 4502276 InventorsAssigneeApplicationNo. 06/797805 filed on 11/13/1985US Classes:60/796, Having mounting or supporting structure415/199.4, Including an axial-flow blade set415/213.1, Casing with mounting means415/220Casing with axial flow runnerExaminersPrimary: Casaregola, Louis J.Assistant: Stout, Donald E. Attorney, Agent or FirmInternational ClassesF01D 25/26 (20060101)F01D 25/24 (20060101) F02C 7/20 (20060101) Foreign Application Priority Data1984-12-08 GBAbstractThe casings of gas turbine engines are subject to loadings which distort the casing and adversely affect the running clearance between rotating and static components contained within the casings. The invention provides an engine having inner and outer housings the inner housing containing one of the engine compressors. The inner casing is mounted on a load transmitting and isolating structure which allows thrust and torque to be transmitted to the outer casing, but isolates the inner casing from distortions of the outer casing. The load transmitting and isolating structure includes a torque reaction and mounting means at the upstream end of the inner casing, a mounting means and a thrust reacting means mounted between the ends of the inner casing. The mounting means are adjacent the bearings of the rotor shaft of the compressor and are not affected to any appreciable extent by outer casing distortion. The thrust reacting means are mounted in a horizontal plane and are not affected by bending of the outer casing in a vertical plane. | |