Search

CN-116223045-B - Full-size aeroengine nacelle acoustic test platform

CN116223045BCN 116223045 BCN116223045 BCN 116223045BCN-116223045-B

Abstract

The application belongs to the technical field of acoustic tests, and particularly relates to a full-size aero-engine nacelle acoustic test platform. Comprises an air inlet channel acoustic liner assembly, a first flange section, an air inlet channel measuring section, an aeroengine noise simulation section, an exhaust channel measuring section, a second flange section and an air outlet channel acoustic liner assembly which are sequentially connected from the front end to the rear end, and the hub is hung on the second flange section and the exhaust channel acoustic liner assembly, and the hub and the exhaust channel acoustic liner assembly are coaxially arranged. The full-size aeroengine nacelle acoustic test platform can simulate the working environment of an aeroengine under a real scale in a laboratory environment, and can be used for simultaneously installing an air inlet channel acoustic liner and an air outlet channel acoustic liner of the nacelle and testing the acoustic performance effect of the nacelle.

Inventors

  • LI ZHUOHAN
  • WANG LONG
  • YAN QUN
  • XUE DONGWEN
  • YANG JIAFENG
  • WEI KAI
  • XU JIAN
  • CHEN YONGHUI

Assignees

  • 中国飞机强度研究所

Dates

Publication Date
20260505
Application Date
20230120

Claims (10)

  1. 1. The utility model provides a full-size aeroengine nacelle acoustic test platform which characterized in that includes: the front end of the air inlet channel measuring section (3) is connected with the air inlet channel acoustic liner assembly (1) through the first flange section (2); The front end of the aero-engine noise simulation section (4) is connected with the rear end of the air inlet channel measurement section (3); The front end of the exhaust passage measuring section (5) is connected with the rear end of the aeroengine noise simulation section (4), and the rear end of the exhaust passage measuring section (5) is connected with an exhaust passage acoustic liner assembly (7) through a second flange section (6); The hub (8) is hung on the second flange section (6) and the exhaust channel acoustic liner assembly (7), and the hub (8) and the exhaust channel acoustic liner assembly (7) are coaxially arranged; The air inlet channel acoustic liner assembly (1), the first flange section (2), the air inlet channel measuring section (3), the aeroengine noise simulation section (4), the exhaust channel measuring section (5), the second flange section (6), the exhaust channel acoustic liner assembly (7) and the hub (8) form an integral structure, and the integral structure is fixed on a bottom frame (9) through a plurality of support arms.
  2. 2. The full-size aero-engine nacelle acoustic test platform of claim 1, wherein the support arms comprise six support arms, and the six support arms are divided into three groups, and the first flange section (2), the aero-engine noise simulation section (4), and the second flange section (6) are fixedly connected with the bottom frame (9) respectively.
  3. 3. The full-size aeroengine nacelle acoustic test platform of claim 2, further comprising an electric flatbed (10), the bottom frame (9) being mounted on the electric flatbed (10).
  4. 4. The full-size aircraft engine nacelle acoustic test platform of claim 3, wherein the intake runner acoustic liner assembly (1) comprises a first acoustic liner panel, an intake runner acoustic liner, a first mounting frame, and a first lip, wherein, The air inlet channel acoustic liner is inserted into the first installation frame, the front end of the first installation frame is provided with the first lip, the rear end of the first installation frame is provided with the first acoustic liner plate, and the rear end of the first installation frame is connected with the first flange section (2) through the flange plate.
  5. 5. The full-size aircraft engine nacelle acoustic test platform of claim 1 wherein, The air inlet channel measuring section (3) realizes the characteristic test of a forward transmission noise source and a backward transmission noise source sent by the aeroengine noise simulation section (4) through a microphone array; and the exhaust passage measuring section (5) is used for realizing the characteristic test of the forward and backward noise sources sent by the aeroengine noise simulation section (4) through a microphone array.
  6. 6. Full-size aero-engine nacelle acoustic test platform according to claim 1, wherein the aero-engine noise simulation section (4) is acoustic by means of a rotary modal generator or a rotor fan.
  7. 7. The full-size aeroengine nacelle acoustic test platform according to claim 6, wherein the rotational mode generator comprises a simulation pipeline (43), a plurality of waveguides (42) are uniformly distributed on the circumference of the simulation pipeline (43), and a loudspeaker (41) is arranged on the waveguides (42).
  8. 8. The full-size aircraft engine nacelle acoustic test platform of claim 6, wherein the rotor fan comprises a rotor nose cone (44), a single stage rotor fan (45), a single stage stator fan (46), a rear hub (47), and a hub shell (48) mounted on the single stage stator fan (46) connected in sequence.
  9. 9. The full-size aircraft engine nacelle acoustic test platform of claim 7, wherein the exhaust duct acoustic liner assembly (7) comprises a second acoustic liner panel (71), an exhaust duct acoustic liner (72), a second mounting frame (73), and a second lip (74), wherein, The exhaust channel acoustic liner (72) is inserted into the second mounting frame (73), the second acoustic liner plate (71) is mounted at the front end of the second mounting frame (73), the second lip (74) is mounted at the rear end of the second mounting frame (73), and the front end of the second mounting frame (73) is connected with the second flange section (6) through a flange plate.
  10. 10. The full-size aeroengine nacelle acoustic test platform according to claim 9, wherein the hub (8) comprises a front end hemisphere (81), a hub intermediate body (82) and a tail cone (83), the front end of the hub intermediate body (82) extends forward to form a butt-joint ring, the butt-joint ring is connected with the front end hemisphere (81) through a radially mounted screw, the rear end of the hub intermediate body (82) is connected with the tail cone (83) through an inner flange, the front end of the hub intermediate body (82) is hung on the second flange section (6) through a stud, and the rear end is hung on the second lip (74) through the stud.

Description

Full-size aeroengine nacelle acoustic test platform Technical Field The application belongs to the technical field of acoustic tests, and particularly relates to a full-size aero-engine nacelle acoustic test platform. Background The installation of an aircraft engine nacelle acoustic liner is one of the effective methods of reducing aircraft engine noise. For acoustic performance testing of the acoustic liner of the nacelle, a flat acoustic liner test, a reduced scale acoustic liner test and other methods are generally adopted to test the acoustic liner performance. The flat acoustic liner is used for testing the impedance characteristic of the acoustic liner, and the reduced scale acoustic liner test is used for testing the acoustic performance of a single (air inlet channel acoustic liner or air outlet channel acoustic liner) acoustic liner under the reduced scale condition. With respect to the existing acoustic liner testing technology, no acoustic liner testing technology is available which can simulate the dimensions of a real nacelle of an aircraft engine or test the acoustic performance under the condition of simultaneously installing an air inlet acoustic liner and an exhaust acoustic liner. It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art. Disclosure of Invention The application aims to provide a full-size aero-engine nacelle acoustic test platform to solve at least one problem existing in the prior art. The technical scheme of the application is as follows: A full-size aircraft engine nacelle acoustic test platform comprising: The front end of the air inlet channel measuring section is connected with the air inlet channel acoustic liner assembly through a first flange section; The front end of the aero-engine noise simulation section is connected with the rear end of the air inlet channel measurement section; the front end of the exhaust passage measuring section is connected with the rear end of the aeroengine noise simulation section, and the rear end of the exhaust passage measuring section is connected with the exhaust passage acoustic liner assembly through a second flange section; The hub is hung on the second flange section and the exhaust channel acoustic liner assembly, and the hub and the exhaust channel acoustic liner assembly are coaxially arranged; The air inlet channel acoustic liner assembly, the first flange section, the air inlet channel measuring section, the aeroengine noise simulation section, the exhaust channel measuring section, the second flange section, the air outlet channel acoustic liner assembly and the hub form an integral structure which is fixed on a bottom frame through a plurality of support arms. In at least one embodiment of the present application, the support arms include six, and the six support arms are divided into three groups, and the first flange section, the aero-engine noise simulation section, and the second flange section are fixedly connected with the bottom frame, respectively. In at least one embodiment of the present application, an electric flat car is further included, and the bottom frame is mounted on the electric flat car. In at least one embodiment of the present application, the inlet liner assembly comprises a first liner panel, an inlet liner, a first mounting frame, and a first lip, wherein, The air inlet channel acoustic liner is inserted into the first installation frame, the front end of the first installation frame is provided with the first lip, the rear end of the first installation frame is provided with the first acoustic liner plate, and the rear end of the first installation frame is connected with the first flange section through the flange plate. In at least one embodiment of the present application, The air inlet channel measuring section realizes the characteristic test of a forward transmission noise source and a backward transmission noise source sent by the aeroengine noise simulation section through a microphone array; and the exhaust passage measuring section realizes the characteristic test of the forward transmission noise source and the backward transmission noise source sent by the aeroengine noise simulation section through the microphone array. In at least one embodiment of the application, the acoustic source of the aero-engine noise simulation section is provided by a rotary mode generator or a rotor fan. In at least one embodiment of the present application, the rotary mode generator includes a simulation pipe, and a plurality of waveguides are uniformly distributed on the circumference of the simulation pipe, and speakers are disposed on the waveguides. In at least one embodiment of the present application, the rotor fan includes a rotor nose cone, a single stage rotor fan, a single stage stator fan, a rear hub, and a hub housing mounted on the single stage stator fan, which are connected in sequence. In at least