Aeronautics and astronautics – Aircraft power plants – Mounting
Patent
1991-06-27
1993-02-02
Peters, Jr., Joseph F.
Aeronautics and astronautics
Aircraft power plants
Mounting
60 3931, 248554, B64D 2700
Patent
active
051832232
ABSTRACT:
A support system for the aft end of fan jet gas turbine engines which reduces engine bending in operation while accommodating radial and longitudinal thermal expension forces. A first radial ring secured to the engine structure core cowl and the overall engine support pylon has a plurality of spaced longitudinal grooves. A second, cooperating radial ring secured to the engine has a plurality of outwardly extending tabs sized to fit within the first ring grooves. The tabs do not extend fully into the grooves at ambient temperatures. When operation of the engine begins, the engine heats up to a relatively high temperature. Radial thermal expansion is accommodated by expansion of the inner ring, causing the tabs to move deeper into the grooves. Longitudinal thermal expansion is accommodated by slippage of the tabs along the grooves in a longitudinal direction. Meanwhile, the engine is supported against bending and flexing beyond the amount permitted by the space between tab ends and bottoms of the grooves.
REFERENCES:
patent: 3979087 (1976-09-01), Boris et al.
patent: 4458863 (1984-07-01), Smith
patent: 4683717 (1987-08-01), Naud
patent: 5004402 (1991-04-01), Burchette et al.
Bidwell Anne E.
Gilliam Frank D.
Peters Jr. Joseph F.
Rohr Inc.
Schlesinger Patrick J.
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