Turbomachine test bench with active noise control

Patent metadata

Field	Value
Publication number	US-10161267-B2
Application number	US-201715683881-A
Country	US
Kind code	B2
Filing date	Aug 23, 2017
Priority date	Sep 5, 2016
Publication date	Dec 25, 2018
Grant date	Dec 25, 2018

Abstract

A test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. The system reduces the turbomachine waves on the basis of the measurements from the first microphone and from the second microphone. The invention also proposes a method for attenuating the noise emissions from the turbomachine tested in the test bench.

First claim

What is claimed is:

1. A test bench for an aircraft turbojet, said test bench comprising:
an installation zone for an aircraft turbojet; and
an active system for attenuating sound waves emitted by the aircraft turbojet, the active system including a first microphone placed downstream of the installation zone of the aircraft turbojet, and an attenuation zone for attenuating the sound waves of the aircraft turbojet with an emitter for emitting attenuation sound waves;
wherein
the active system further comprises a second microphone placed downstream of the attenuation zone, and
the active system being configured to attenuate the sound waves of the aircraft turbojet as a function of measurements from the first microphone and from the second microphone,
wherein the attenuation zone is situated between the first microphone and the second microphone,
the bench further comprising a tube for collecting the airflow propelled by the aircraft turbojet downstream of the installation zone for the aircraft turbojet, the attenuation zone being arranged along the tube,
the bench further comprising two bulkheads defining a chamber for the emitter, the first microphone and the second microphone being outside of the chamber.

2. The test bench according to claim 1 , wherein the first microphone is placed upstream of the tube and upstream of the attenuation zone.

3. The test bench according to claim 1 , wherein the second microphone is placed downstream of the tube.

4. The test bench according to claim 1 further comprising a structural wall downstream of the tube, the second microphone being closer to the tube than to the structural wall, the structural wall being perpendicular to the main elongation of the test bench.

5. The test bench according to claim 1 further comprising a passage for a flow from the turbomachine, the first microphone and the second microphone being placed in the passage.

6. The test bench according to claim 1 , wherein the first microphone and the second microphone are axially spaced from each other by a distance longer than or equal to 16 feet (5 meters).

7. The test bench according to claim 1 , wherein the turbomachine has an axis of rotation and the installation zone for turbomachine includes a central axis coaxial to the axis of rotation of the turbomachine, at least one or each microphone being placed on the central axis.

8. The test bench according to claim 1 , wherein the turbomachine has an axis of rotation and the installation zone for turbomachine includes a central axis that is one of coaxial or parallel to the axis of rotation of the turbomachine, at least one or each microphone being offset by less than 3 feet (1 m) relative to the central axis.

9. The test bench according to claim 1 further comprising a straight corridor in which the installation zone for turbomachine and the second microphone are arranged.

10. A test bench for an aircraft turbojet, said test bench comprising:
an installation zone for an aircraft turbojet;
an active system for attenuating sound waves emitted by the aircraft turbojet, the active system including a first microphone placed downstream of the installation zone of the aircraft turbojet, and an attenuation zone for attenuating the sound waves of the aircraft turbojet with an emitter for emitting attenuation sound waves;
a second microphone placed downstream of the attenuation zone;
a tube for collecting the airflow propelled by the aircraft turbojet downstream of the installation zone for the aircraft turbojet, the attenuation zone being arranged along the tube;
two bulkheads defining a chamber for the emitter; and

chimneys with passive systems for attenuating a noise propagating out of the test bench, the second microphone being directly below one of the chimneys outside of the bulkhead.

11. The test bench according to claim 10 , wherein the first microphone is placed outside the chimneys.

Assignees

• Safran Aero Boosters Sa

Inventors

• Meys Benoit
• Lacroix Alain

Classifications

• F05D2260/962

  by means of "anti-noise" · CPC title

• G10K11/178

  by electro-acoustically regenerating the original acoustic waves in anti-phase · CPC title

• F02K1/44

  Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction (F02K1/40 takes precedence) · CPC title

• G10K2210/121

  Rotating machines, e.g. engines, turbines, motors; Periodic or quasi-periodic signals in general · CPC title

• F05D2270/333

  Noise or sound levels · CPC title