Bypass lip seal
First Claim
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1. A cooling apparatus for cooling a fluid in a bypass gas turbine engine, said apparatus comprising:
- a heat exchanger defining a fluid passage, said heat exchanger being disposed within a bypass duct and being exposed to a bypass air flow; and
a flow divider affixed to an annular wall of said bypass duct, in combination with said wall of said bypass duct forming a sub-passage for accommodating said heat exchanger, said sub-passage defining an open upstream end and an open downstream end to direct a portion of said bypass air flow to pass therethrough.
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Abstract
A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided.
69 Citations
18 Claims
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1. A cooling apparatus for cooling a fluid in a bypass gas turbine engine, said apparatus comprising:
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a heat exchanger defining a fluid passage, said heat exchanger being disposed within a bypass duct and being exposed to a bypass air flow; and a flow divider affixed to an annular wall of said bypass duct, in combination with said wall of said bypass duct forming a sub-passage for accommodating said heat exchanger, said sub-passage defining an open upstream end and an open downstream end to direct a portion of said bypass air flow to pass therethrough. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A gas turbine engine comprising:
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a core engine; a bypass duct surrounding said core engine and adapted to direct a bypass air flow through said bypass duct; a heat exchanger defining a fluid passage, said heat exchanger being disposed within said bypass duct and being exposed to said bypass air flow; and means for increasing a local pressure differential of said bypass air flow between upstream and downstream locations with respect to said heat exchanger in order to facilitate heat exchange between said heat exchanger and said air flow. - View Dependent Claims (8, 9, 10, 11, 12)
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13. A method of installing a fluid cooling apparatus in a gas turbine engine, said method comprising:
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1) placing a heat exchanger into a bypass duct through an open area of an outer annular wall of said bypass duct and positioning said heat exchanger in a sub-passage defined within said bypass duct; and 2) closing said open area of said outer wall of said bypass duct, said heat exchanger being connectable to a fluid circuit of said engine. - View Dependent Claims (14, 15)
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16. A seal assembly for a gas turbine engine bypass duct cooler, said assembly comprising:
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a bypass duct cooler having a peripheral recess; a body having an opening, said opening bounded by a peripheral flange arranged angularly to a surface of said body, said recess and flange being configured such that said flange is receivable within said recess; and a seal disposed within said recess substantially continuously around the periphery, said seal adapted to sealingly engage said flange when said recess is mated with said flange. - View Dependent Claims (17, 18)
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Specification