Control of flow instabilities in turbomachines

• US 5,230,603 A
• Filed: 08/13/1991
• Issued: 07/27/1993
• Est. Priority Date: 08/22/1990
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Day, Ivor J.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Mattingly, Todd
• Application Number:
  US07/744,439
• Time in Patent Office: 714 Days
• Field of Search: 416/245 R, 416/94, 415/26, 415/180, 415/183, 415/185, 415/914, 415/119, 415/125, 415/118, 244/134 A
• US Class Current: 415/26
• CPC Class Codes: B64D 2033/0286 for turbofan engines
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: F02C 7/042 having variable geometry
• CPC Class Codes: F04D 27/0246 by varying geometry within the pumps, e.g. by adjusting vanes
• CPC Class Codes: F04D 29/681 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/682 by fluid extraction
• CPC Class Codes: F04D 29/684 by fluid injection
• CPC Class Codes: F05D 2260/962 by means of "anti-noise"

Abstract

To control unsteady motion phenomena in turbomachines, it has been proposed to employ an active control system to modify the flow conditions. In the present invention, the modification is effected by devices mounted in a bullet or nose bullet at the entry to a rotor of the turbomachine.

Claims

1. A control system for a turbomachine having a front fan and a core engine containing further compressor stages, the front fan feeding part of its output to the core engine, the control system for modifying fluid flow through the turbomachine, the turbomachine having rotor blading for compressing the flow through the turbomachine and nose bullet means attached to the fan upstream of the blading, the control system comprising:

sensor means located to sense precursory disturbances in the flow of fluid past the blading, said precursory disturbances being disturbances which develop into unstable flow conditions deleterious to the proper working of the compressor stages;

actuator means for generating corrective disturbances in the flow of fluid past the blading, the corrective disturbances being corrective to the precursory disturbances; and

signal processing means for driving the actuator means in dependence upon the sensor signals to produce the corrective disturbances, wherein the nose bullet means includes the actuator means, the actuator means being constructed to transiently change the effective profile of an external surface of the bullet means relative to the flow of fluid thereover when driven by the signal processing means, whereby the corrective disturbances are produced in the flow of fluid over the surface of the nose bullet means before the fluid encounters the blading, and the corrective disturbances passing between adjacent fan blades adjacent their radially inner ends without adversely effecting the performance of the fan, to thereby enter the core engine to modify fluid flow therein.

2. A turbomachine according to claim 1 wherein the actuator means comprises a plurality of displaceable flaps.

3. A turbomachine according to claim 1 wherein the actuator means comprises fluid blowing means.

4. A turbomachine according to claim 1 wherein the actuator means comprises fluid suction means.

5. A turbomachine according to claim 1 wherein the actuator means comprises at least one pressure wave generating device.

6. A turbomachine according to claim 1 wherein the actuator means comprises means for elastically deforming the external shape of said bullet or nose bullet.

7. A turbomachine according to claim 1 wherein the actuator means comprise means for gyrating said nose bullet about the rotor axis.