초록 ▼

A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow us

A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine.

대표청구항 ▼

1. A gas turbine engine comprising a fan assembly, a compressor assembly, a combustion gas generator assembly, a turbine assembly and an annular bypass air duct for directing a bypass air flow driven by the fan assembly to pass therethrough, the annular bypass air duct being defined between inner an

1. A gas turbine engine comprising a fan assembly, a compressor assembly, a combustion gas generator assembly, a turbine assembly and an annular bypass air duct for directing a bypass air flow driven by the fan assembly to pass therethrough, the annular bypass air duct being defined between inner and outer duct walls, a plurality of struts radially extending between the inner and outer duct walls, at least one of the struts having an aerodynamic fairing located the bypass air duct, the at least one strut including an air scoop in the fairing, the air scoop defined at a mid span of the fairing and at a leading edge of the fairing, the air scoop in fluid communication with an air passage leading to the turbine assembly. 2. The gas turbine engine as defined in claim 1 wherein the at least one strut has a hollow portion accommodating a section of the air passage. 3. The gas turbine engine as defined in claim 1 wherein the air scoop is defined as an opening in a wall of the leading edge of the at least one strut. 4. The gas turbine engine as defined in claim 1 wherein the at least one strut comprises a valve for selectively closing the scoop. 5. The gas turbine engine as defined in claim 4 wherein the valve provides part of an outer perimeter of the fairing when the valve closes the scoop. 6. The gas turbine engine as defined in claim 5 wherein the valve is radially slidable between a first position in which the scoop is open and a second position in which the scoop is closed. 7. The gas turbine engine as defined in claim 5 wherein the valve is rotatable about a axis between a first position in which the scoop is open and a second position in which the scoop is closed. 8. A gas turbine engine comprising: an cooling air passage extending from an engine air duct to a turbine shroud for directing a portion of an air flow to the turbine shroud for selectively cooling the turbine shroud;an air scoop incorporated in an aerodynamic fairing of a strut radially extending within the air duct and in fluid communication with the cooling air passage, the air scoop being defined at a mid span of the air fairing and facing the air flow in order to scoop the portion of the air flow into the cooling air passage with a maximum dynamic pressure available in the air flow;a valve member for selectively completely opening and completely closing the air scoop; andan apparatus for controlling operation of the valve member. 9. The gas turbine engine as defined in claim 8 wherein the air duct is an annular bypass air duct for directing a bypass air flow. 10. The gas turbine engine as defined in claim 9 wherein the strut comprises a hollow configuration accommodating a section of the cooling air passage, the air scoop being defined as an opening in a wall of the strut. 11. The gas turbine engine as defined in claim 10 wherein the valve member is configured as a substantial part of the air fairing of the strut when the valve member closes the opening. 12. The gas turbine engine as defined in claim 10 wherein the valve member is radially slidable between a first position in which the opening is fully accessible for the scooped portion of the bypass air flow to enter the air passage and a second position in which the opening is completely blocked. 13. The gas turbine engine as defined in claim 10 wherein the valve member is rotatable about a radial axis, between a first position in which the opening is fully accessible for the scooped portion of the bypass air flow to enter the air passage and a second position in which the opening is completely blocked. 14. The gas turbine engine as defined in claim 10 wherein the means for controlling operation of the valve member comprises an valve actuator having a linkage extending within the hollow configuration of the strut to connect with the valve member for operation. 15. The gas turbine engine as defined in claim 14 wherein the valve actuator is controlled by an engine electronic controller (EEC).