| CPC F02C 7/20 (2013.01) [F02C 7/18 (2013.01); F02C 7/185 (2013.01); F05D 2240/91 (2013.01); F05D 2260/213 (2013.01); F05D 2260/96 (2013.01)] | 14 Claims |
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1. A gas turbine engine comprising
a bypass duct arranged circumferentially around a central axis of the gas turbine engine, the bypass duct including an outer wall assembly defining an outer boundary of a flow path and an inner wall defining an inner boundary of the flow path, the outer wall assembly including a main annular wall body and an access panel removably coupled to the main annular wall body, the bypass duct configured to direct bypass air from an inlet of the gas turbine engine through the flow path,
a heat exchanger arranged within the bypass duct and coupled to the access panel, the heat exchanger configured to receive at least a portion of the bypass air and to transfer heat from a cooling fluid passing through the heat exchanger to the portion of the bypass air, and
a first turnbuckle assembly that couples the heat exchanger to the access panel, the first turnbuckle assembly including a first turnbuckle rod coupled to the access panel at a radially outer end of the first turnbuckle rod and a second turnbuckle rod coupled to the first turnbuckle rod and to the heat exchanger at a radially inner end of the second turnbuckle rod, wherein the radially outer end of the first turnbuckle rod is threadably received in and engaged with a first threaded socket of a first socket housing removably coupled to the access panel such that the first turnbuckle rod is fixedly coupled to the first socket housing so as to increase lateral stiffness of the heat exchanger and the first turnbuckle assembly such that the lateral dynamic mode is outside of a fan rotor operating range of the gas turbine engine.
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