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EP-4741288-A1 - COMBINED ENGINE AND AIRCRAFT

EP4741288A1EP 4741288 A1EP4741288 A1EP 4741288A1EP-4741288-A1

Abstract

This combined engine includes a flow path part having a first and second flow paths, a first engine, and a second engine, as well as a switching part. The switching part includes: a rotation member capable of rotating between a first position for opening the first flow path and a second position for closing the first flow path; and a slide member for rotating the rotation member between the first position and the second position.

Inventors

  • TAGUCHI, HIDEYUKI
  • IMAMURA, Shunsuke
  • TOMIOKA, Sadatake

Assignees

  • Japan Aerospace Exploration Agency

Dates

Publication Date
20260513
Application Date
20240410

Claims (12)

  1. A combined engine to be mounted on an aircraft, the combined engine comprising: a first engine corresponding to a first speed range; a second engine corresponding to a second speed range higher than the first speed range; a flow passage section including a first flow passage that is an air flow passage of the first engine and a second flow passage that is an air flow passage of the second engine; and a switching section capable of switching between opening and closing of the first flow passage in the flow passage section, wherein the switching section includes: a pivotable member that is pivotable between a first position where the first flow passage is opened and a second position where the first flow passage is closed, and a slide member that moves slidingly to pivot the pivotable member between the first position and the second position.
  2. The combined engine according to claim 1, wherein: the pivotable member is configured to be pivotable about a base end portion, and the switching section includes: a guide rail that extends in a predetermined direction and on which the slide member moves slidingly, and a link member that links the slide member with a portion of the pivotable member other than the base end portion so as to pivot the pivotable member by movement of the slide member.
  3. The combined engine according to claim 2, wherein: the flow passage section is configured as a housing including the first engine, the second engine, and the switching section, the flow passage section includes an isolation wall that isolates the first engine and the second engine from each other, and the isolation wall supports the base end portion such that the pivotable member is pivotable.
  4. The combined engine according to claim 3, wherein the switching section is provided at each of an air inlet of the flow passage section and an air outlet of the flow passage section.
  5. The combined engine according to claim 2, further comprising: a facing member that is disposed at a position facing the pivotable member and that constitutes a part of at least one flow passage of the first flow passage and the second flow passage between the facing member and the pivotable member, wherein the facing member is disposed on the slide member to be capable of changing its orientation in conjunction with the movement of the slide member.
  6. The combined engine according to claim 5, wherein the facing member is disposed in such an orientation that a second force in a direction canceling a first force applied to the slide member due to air in the at least one flow passage acts on the slide member.
  7. The combined engine according to claim 1, further comprising: a tubular housing that includes the first engine, the second engine, and the flow passage section, wherein a first inlet of air in the first flow passage and a second inlet of air in the second flow passage are disposed in a leading end portion of the housing at different positions, and the pivotable member includes a closing portion that is capable of closing any one of the first inlet and the second inlet.
  8. The combined engine according to claim 7, wherein one end of the slide member is attached to the pivotable member, and the slide member pivots the pivotable member by extending and contracting.
  9. The combined engine according to claim 1, wherein the aircraft is a supersonic aircraft.
  10. The combined engine according to claim 9, wherein the aircraft is a hypersonic aircraft.
  11. An aircraft, comprising: an airframe; and the combined engine according to claim 1 that is provided on a lower surface of the airframe, wherein a surface of the lower surface of the airframe which extends from a nose section of the airframe to the combined engine is inclined to be located lower toward the combined engine from the nose section.
  12. The aircraft according to claim 11, wherein an angle of the surface with respect to a horizontal direction is smaller than an angle, with respect to the horizontal direction, of a line connecting the nose section of the airframe and a lower edge portion of an air inlet of the combined engine.

Description

Technical Field The present disclosure relates to a combined engine and an aircraft. Background Art In the related art, an aircraft including a combined engine is known (for example, see Patent Literature (hereinafter, referred to as "PTL") 1. The combined engine includes a plurality of engines corresponding to a plurality of speed ranges. In the combined engine, a movable element that can switch between opening and closing of an air flow passage of each of the plurality of engines is provided. In this configuration, the movable element pivots up and down to switch between two air flow passages. Citation List Patent Literature PTL 1 Japanese Patent Application Laid-Open No. 2004-270691 Summary of Invention Technical Problem However, since the movable element is subjected to pressure, the movable element is difficult to operate due to the influence of the pressure in a case of switching the air flow passage, and as a result, there is a problem that the switching of the flow passage cannot be smoothly performed. Since the configuration disclosed in PTL 1 does not disclose a mechanism for pivoting the movable element, the above-described problem cannot be solved. An object of the present disclosure is to provide a combined engine and an aircraft capable of smoothly switching a flow passage. Solution to Problem A combined engine according to the present disclosure is a combined engine to be mounted on an aircraft, and includes: a first engine corresponding to a first speed range;a second engine corresponding to a second speed range higher than the first speed range;a flow passage section including a first flow passage that is an air flow passage of the first engine and a second flow passage that is an air flow passage of the second engine; anda switching section capable of switching between opening and closing of the first flow passage in the flow passage section, whereinthe switching section includes: a pivotable member that is pivotable between a first position where the first flow passage is opened and a second position where the first flow passage is closed, anda slide member that moves slidingly to pivot the pivotable member between the first position and the second position. An aircraft according to the present disclosure includes: an airframe; andthe combined engine described above that is provided on a lower surface of the airframe, whereina surface of the lower surface of the airframe which extends from a nose section of the airframe to the combined engine is inclined to be located lower toward the combined engine from the nose section. Advantageous Effects of Invention According to the present disclosure, the flow passage can be smoothly switched. Brief Description of Drawings FIG. 1 is a diagram showing an aircraft including a combined engine according to Embodiment 1 of the present disclosure;FIG. 2 is a perspective view of the aircraft as viewed from below;FIG. 3 is a side view of the aircraft;FIG. 4 is a side view of the aircraft;FIG. 5 is a perspective view of a first switching section;FIG. 6 is a side view of the first switching section at a first position;FIG. 7 is a side view of the first switching section at a second position;FIG. 8 is a perspective view of a second switching section;FIG. 9 is a side view of the second switching section at a third position;FIG. 10 is a side view of the second switching section at a fourth position;FIG. 11 is a diagram showing an aircraft including a combined engine according to Embodiment 2 of the present disclosure;FIG. 12 is a side cross-sectional view of a first duct portion in the combined engine;FIG. 13 is a side cross-sectional view of a second duct portion in the combined engine;FIG. 14 is a diagram showing a switching section in a state where a first inlet is opened; andFIG. 15 is a diagram showing a switching section in a state where a second inlet is opened. Description of Embodiments Embodiment 1 of the present disclosure is elaborated below with reference to the drawings. FIG. 1 is a diagram showing an aircraft including a combined engine according to Embodiment 1 of the present disclosure. In addition, in describing a structure of aircraft 1 of the present embodiment, a rectangular coordinate system shown in each drawing will be used. Aircraft 1 is disposed such that, for example, when aircraft 1 is located on the ground, the X direction is a front-rear direction, the Y direction is a left-right direction, and the Z direction is an up-down direction. As shown in FIG. 1, aircraft 1 is, for example, a hypersonic aircraft capable of flying at a hypersonic speed of Mach 5 or more in the atmosphere, and includes airframe 10 and combined engine 100. Aircraft 1 has a shape (so-called waverider configuration) in which a pressure on a lower surface of airframe 10 is increased by a shock wave generated at a leading edge of airframe 10 (main wing portion) to generate a large lift. Airframe 10 is configured to have a substantially triangular shape as viewed