[특허]Apparatus and methods for varying inlet lip geometry of a jet engine inlet

The Boeing Company

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Apparatus and methods for varying inlet lip geometry of a jet engine inlet

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/04
미국특허분류(USC)	060/204; 060/269; 244/053.B; 137/015.1
출원번호	US-0628620 (2003-07-28)
발명자 / 주소	Sakurai, Seiya Fox, Stephen J. Grimlund, Kristin E.
출원인 / 주소	The Boeing Company
대리인 / 주소	Harness Dickey &
인용정보	피인용 횟수 : 6 인용 특허 : 7

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Apparatus for varying inlet lip geometry of a inlet formed at forward end portion of a jet engine housing. In one embodiment, the apparatus includes a variable camber skin portion hingedly coupled to the forward end portion of the housing. The apparatus also includes a linkage assembly coupled to the forward end portion and the skin portion. The linkage assembly operates to rotate the skin portion relative to the forward end portion and to alter a curvature of the skin portion to thereby configure the skin portion into a corresponding one of a plurality of configurations. The plurality of configurations include at least a first configuration and a second configuration. In the first configuration, the skin portion forms a rounded inlet lip portion extending forwardly of the inlet. In the second configuration, the linkage assembly and the skin portion are retracted within a recessed area in the housing to form an aerodynamically smooth outer surface of the housing.

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1. An inlet for a jet engine having variable geometry to alter airflow, the inlet comprising:lip structure defining the inlet, the lip structure comprising a wall that includes an inner surface and an outer surface, the outer surface comprising: a first portion; and a second portion that is pivotally coupled to the inner surface at a forward end with a hinge and is separable from the first portion at an aft end; and an actuator structure associated with the outer surface second portion and operable to vary the geometry of the inlet by pivoting the outer surface second portion about the hinge at the forward end such that the aft end separates from the outer surface first portion, moving outwardly and forward from the outer surface first portion, so that the outer surface second portion forms an extension of the inner surface projecting forward of the forward end. 2. The inlet of claim 1, wherein the geometry of the inlet is variable between at least:a first configuration in which the outer surface second portion projects forward of the outer surface second portion forward end to form a rounded inlet lip; and a second configuration in which the outer surface second portion is retracted such that the outer surface second portion aft end aligns with the outer surface first portion to form an aerodynamically smooth outer surface. 3. The inlet of claim 2, wherein the actuator structure is coupled to the outer surface second portion at two points to alter the curvature of the outer surface second portion forward end about the two points when in the first configuration.4. The inlet of claim 1, wherein the actuator structure includes a linkage assembly.5. The inlet of claim 4, wherein the linkage assembly includes a four-bar linkage.6. The inlet of claim 1, wherein the inlet comprises a side inlet.7. A jet engine for a mobile platform, the engine comprising:a housing including an inlet having a wall that includes an inner surface and an outer surface; a variable camber skin portion of the outer surface that is hingedly coupled to the inner surface at a forward end and separable from a static portion of the outer surface at an aft end; a linkage assembly retractable within a recess of the inlet wall and coupled to the the camber skin portion, the linkage assembly operating to rotate the camber skin portion at the forward end such that the aft end separates from outer surface static portion, moving outwardly and forward from the outer surface static portion, so that the camber skin portion forms an extension of the inner surface that project forward of the camber skin portion forward end to alter a curvature of the camber skin portion thereby configuring the camber skin portion to form a rounded inlet lip. 8. The engine of claim 7, wherein the linkage assembly is further operable to retract within the recess to move the camber skin portion from projecting forward of the camber skin portion forward end to a retracted position in which the camber skin portion aft end aligns with the outer surface static portion to form an aerodynamically smooth outer surface.9. The engine of claim 8, wherein:the mobile platform comprises an aircraft; the camber skin portion is protected forward during takeoff and landing of the aircraft; and the camber skin is retracted while the aircraft is in a cruise mode of operation. 10. The engine of claim 7, wherein the linkage assembly is coupled to the camber skin portion at two points to alter the curvature of the skin portion about the two points.11. The engine of claim 7, further comprising an actuator coupled to the linkage assembly for extending and retracting the linkage assembly.12. The engine of claim 11, wherein the linkage assembly includes a four-bar linkage.13. The engine of claim 7, wherein the housing comprises a nacelle.14. The engine of claim 7, wherein the inlet comprises a side inlet.15. The engine of claim 7, wherein:the inlet includes a first inlet lip portion and a second inlet lip portion disposed aft of the first inlet lip portion; and the camber skin portion is included in the second inlet lip portion. 16. An aircraft, comprising:an engine nacelle including an inlet having a wall that includes an inner surface and an outer surface; a variable camber skin portion of the outer surface that is hingedly coupled to the inner surface at a forward end and separable from a static portion of the outer surface at an aft end; a linkage assembly retractable within a recess of the inlet wall and coupled to the camber skin portion, the linkage assembly operating to rotate the camber skin portion at the forward end such that the aft end separates from outer surface static portion, moving outwardly and forward from the outer surface static portion, so that the chamber skin portion forms an extension of the inner surface that projects forward of the camber skin portion forward end to alter a curvature of the camber skin portion thereby configuring the camber skin portion to form a rounded inlet lip. 17. The aircraft of claim 16, wherein the linkage assembly is further operable to retract within the recess to move the camber skin portion from projecting forward of the camber skin portion forward end to a retracted position in which the camber skin portion aft end aligns with the outer surface static portion to form an aerodynamically smooth outer surface.18. The aircraft of claim 17, wherein:the camber skin portion is protected forward during takeoff and landing of the aircraft; and the camber skin is retracted while the aircraft is in a cruise mode of operation. 19. The aircraft of claim 16, wherein the linkage assembly is coupled to the camber skin portion at two points to alter the curvature of the skin portion about the two points.20. The aircraft of claim 16, further comprising an actuator coupled to the linkage assembly for extending and retracting the linkage assembly.21. The aircraft of claim 16, wherein the linkage assembly includes a four-bar linkage.22. The aircraft of claim 16, wherein the inlet comprises a side inlet.23. The aircraft of claim 16, wherein:the inlet includes a first inlet lip portion and a second inlet lip portion disposed aft of the first inlet lip portion; and the camber skin portion is included in the second inlet lip portion. 24. Apparatus for varying inlet lip geometry of an inlet formed at a forward end portion of a housing for a jet engine, the inlet having a wall that includes an inner surface and an outer surface, the apparatus comprising:a variable camber skin portion of the outer surface that is hingedly coupled to the inner surface at a forward end and separable from a static portion of the outer surface at an aft end; a linkage assembly retractable within a recess of the inlet wall and coupled to the camber skin portion, the linkage assembly operating to rotate the camber skin portion at the forward end such that the aft end separates from outer surface static portion, moving outwardly and forward from the outer surface static portion, so that the chamber skin portion forms an extension of the inner surface that project forward of the camber skin portion forward end to alter a curvature of the camber skin portion thereby configuring the camber skin portion to form a rounded inlet lip. 25. The apparatus of claim 24, wherein the linkage assembly is further operable to retract within the recess to move the camber skin portion from projecting forward of the camber skin portion forward end to a retracted position in which the camber skin portion aft end aligns with the outer surface static portion to form an aerodynamically smooth outer surface.26. The apparatus of claim 24, wherein the linkage assembly is coupled to the camber skin portion at two points to alter the curvature of the skin portion about the two points.27. The apparatus of claim 24, further comprising an actuator coupled to the linkage assembly for extending and retracting the linkage assembly.28. The apparatus of claim 27, wherein the linkage assembly includes a four-bar linkage.29. The apparatus of claim 24, wherein the housing comprises a nacelle.30. The apparatus of claim 24, wherein the inlet comprises a side inlet.31. The apparatus of claim 24, wherein:the inlet includes a first inlet lip portion and a second inlet lip portion disposed aft of the first inlet lip portion; and the camber skin portion is included in the second inlet lip portion. 32. A method to increase an area of an inlet of a jet engine housing including an inlet having a wall that includes an inner surface and an outer surface, the method comprising:hingedly coupling a variable camber skin portion of the outer surface to the inner surface at a forward end, the camber skin portion separable from a static portion of the outer surface at an aft end; coupling a linkage assembly to the camber skin portion; and operating the linkage assembly to rotate the camber skin portion at the forward end such that the aft end separates from outer surface static portion, moving outwardly and forward from the outer surface static portion, so that the chamber skin portion forms an extension of the inner surface that project forward of the camber skin portion forward end to alter a curvature of the camber skin portion thereby configuring the camber skin portion to form a rounded inlet lip. 33. The method of claim 32, wherein the linkage assembly is further operable to retract within the recess to move the camber skin portion from projecting forward of the camber skin portion forward end to a retracted position in which the camber skin portion aft end aligns with the outer surface static portion to form an aerodynamically smooth outer surface.34. The method of claim 33, wherein:the jet engine is mounted on an aircraft; the camber skin portion is protected forward during takeoff and landing of the aircraft; and the camber skin is retracted while the aircraft is in cruise mode of operation. 35. The method of claim 32, wherein operating the linkage assembly comprises extending and retracting the linkage assembly.36. The method of claim 35, wherein extending and retracting the linkage assembly comprises actuating an actuator coupled to the linkage assembly.

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Apparatus and methods for varying inlet lip geometry of a jet engine inlet

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Apparatus and methods for varying inlet lip geometry of a jet engine inlet

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이 특허에 인용된 특허 (7)

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IPC 상세정보(version : 201201)

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