GAS TURBINE ENGINE COMPONENT WITH INTEGRAL HEAT EXCHANGER
An assembly is provided for a gas turbine engine (20). This engine assembly includes a vane array (76) and a heat exchanger (74) integrated with the vane array (76). The vane array (76) includes an inner platform (80), an outer platform (82) and a plurality of vanes (84, 86). The inner platform (80)...
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Format: | Patent |
Sprache: | eng ; fre ; ger |
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Zusammenfassung: | An assembly is provided for a gas turbine engine (20). This engine assembly includes a vane array (76) and a heat exchanger (74) integrated with the vane array (76). The vane array (76) includes an inner platform (80), an outer platform (82) and a plurality of vanes (84, 86). The inner platform (80) extends circumferentially about a centerline (28) and forms an inner peripheral boundary of a flowpath through the vane array (76). The outer platform (82) extends circumferentially about the centerline (28) and forms an outer peripheral boundary of the flowpath through the vane array (76). The vanes (84, 86) extend across the flowpath between the inner platform (80) and the outer platform (82). The vanes include a first vane (84) and a second vane (86). The heat exchanger (74) includes a first vane passage (126) and a second vane passage (128) fluidly coupled with and downstream of the first vane passage (126). The first vane passage (126) extends through the first vane (84). The second vane passage (128) extends through the second vane (86). |
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