An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D
An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine.
대표청구항▼
1. An aircraft having an aircraft longitudinal axis and comprising: at least one gas turbine engine having an engine longitudinal axis and comprising at least one compressor or turbine rotor disc defining a respective rotational plane normal to the engine longitudinal axis, wherein the engine longit
1. An aircraft having an aircraft longitudinal axis and comprising: at least one gas turbine engine having an engine longitudinal axis and comprising at least one compressor or turbine rotor disc defining a respective rotational plane normal to the engine longitudinal axis, wherein the engine longitudinal axis is angled relative to the aircraft longitudinal axis such that a respective rotational plane of the respective engine is nonintersecting with one or more of: a further gas turbine engine, a fuel tank, a hydraulic control run, an electrical control run, a passenger or crew compartment, or an aircraft propulsor; andat least one duct arrangement comprising an intake duct leading from an air inlet to an intake of a respective engine, and an exhaust duct leading from an exhaust of the respective engine to an exhaust outlet, wherein the intake duct transitions from a direction generally parallel to the aircraft longitudinal axis at the air inlet, to a direction generally parallel to the respective engine longitudinal axis at the intake, and the outlet duct transitions from a direction generally parallel to the respective engine longitudinal axis at the exhaust of the respective engine, to a direction generally parallel to the aircraft longitudinal axis at the exhaust outlet. 2. An aircraft according to claim 1, wherein aircraft comprises two or more gas turbine engines and associated duct arrangements arranged in a line extending generally normally to the aircraft longitudinal axis in the horizontal plane. 3. An aircraft according to claim 2, wherein the two or more gas turbine engines are arranged in a line substantially coincident with at least one of an aircraft center of mass and an aircraft center of lift. 4. An aircraft according to claim 1, wherein the aircraft comprises one of a blended wing body aircraft and a flying wing aircraft. 5. An aircraft according to claim 1, wherein the engines are located at a trailing edge of the fuselage of the aircraft. 6. An aircraft according to claim 1, wherein the engines are mounted at a point of transition between the fuselage and wings. 7. An aircraft according to claim 1, wherein the engines are located within the aircraft wing or fuselage. 8. An aircraft in accordance with claim 1, wherein the aircraft comprises at least two redundant control runs for at least one aircraft control surface, wherein one control run extends along a first side of an engine, and a further control run extends along a second side of the respective engine. 9. An aircraft according to claim 1, wherein the air inlet of the or each intake duct is located at a leading edge of the point of transition between the fuselage and wings. 10. An aircraft having an aircraft longitudinal axis and comprising: at least two gas turbine engines, each having an engine longitudinal axis and comprising at least one compressor or turbine rotor disc defining a respective rotational plane normal to the engine longitudinal axis, wherein the engine longitudinal axis is angled relative to the aircraft longitudinal axis such that a respective rotational plane of one engine of the at least two gas turbine engines is nonintersecting with any of: another gas turbine engine of the at least two gas turbine engines, a fuel tank, a hydraulic control run, an electrical control run, a passenger or crew compartment, and an aircraft propulsor; andat least one duct arrangement comprising an intake duct leading from an air inlet to an intake of a respective engine, and an exhaust duct leading from an exhaust of the respective engine to an exhaust outlet, wherein the intake duct transitions from a direction generally parallel to the aircraft longitudinal axis at the air inlet, to a direction generally parallel to the respective engine longitudinal axis at the intake, and the outlet duct transitions from a direction generally parallel to the respective engine longitudinal axis at the exhaust of the respective engine, to a direction generally parallel to the aircraft longitudinal axis at the exhaust outlet. 11. An aircraft according to claim 10, wherein aircraft comprises two or more gas turbine engines and associated duct arrangements arranged in a line extending generally normally to the aircraft longitudinal axis in the horizontal plane. 12. An aircraft according to claim 11, wherein the one or more gas turbine engines are arranged in a line substantially coincident with at least one of an aircraft center of mass and an aircraft center of lift. 13. An aircraft according to claim 10, wherein the aircraft comprises one of a blended wing body aircraft and a flying wing aircraft. 14. An aircraft according to claim 10, wherein the engines are located at a trailing edge of the fuselage of the aircraft. 15. An aircraft according to claim 10, wherein the engines are mounted at a point of transition between the fuselage and wings. 16. An aircraft according to claim 10, wherein the engines are located within the aircraft wing or fuselage. 17. An aircraft in accordance with claim 10, wherein the aircraft comprises at least two redundant control runs for at least one aircraft control surface, wherein one control run extends along a first side of an engine, and a further control run extends along a second side of the respective engine. 18. An aircraft according to claim 10, wherein the air inlet of the intake duct is located at a leading edge of the point of transition between the fuselage and wings.
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이 특허에 인용된 특허 (1)
Kress Robert W. (Saugerties NY), Four engine VTOL aircraft.
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