Fan-stator interaction tone reduction

• US 6,409,469 B1
• Filed: 11/21/2000
• Issued: 06/25/2002
• Est. Priority Date: 11/21/2000
• Status: Expired due to Term

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Tse, Man-Chun
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): WOO, RICHARD SUKYOON
• Application Number:
  US09/716,454
• Time in Patent Office: 581 Days
• Field of Search: 415/119, 415/1, 415/199.4, 415/199.5, 415/914, 415/26, 415/47, 415/115, 244/1.N, 416/DIG.2, 416/90.R, 416/91, 416/92, 381/71
• US Class Current: 415/119
• CPC Class Codes: F01D 11/10 using sealing fluid, e.g. steam
• CPC Class Codes: F01D 25/06 for preventing blade vibration means on blade-carrying members or blades F01D5/00
• CPC Class Codes: F02C 7/045 having provisions for noise suppression
• CPC Class Codes: F04D 29/665 by means of resonance chambers or interference
• CPC Class Codes: F04D 29/684 by fluid injection
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: Y10S 415/914 Device to control boundary layer

Abstract

A gas turbine engine rotor assembly such as a fan or compressor includes fan blades spaced axially from stator vanes inside an annular duct. A controlled air blowing system is secured to the annular duct and adapted to blow a hot air flow in a direction opposite to the rotation of the fan blades into the annular duct between the fan blades and the stator vanes, to impart an opposite rotational momentum with respect to the air compressed by the rotor blades, in a asymmetrical pattern to interfere with or destroy a symmetrical pattern of the blade rotation-wake of the compressed air, thereby reducing the strength or preventing the generation of the spinning mode so that the fan-stator interaction tones are significantly reduced.

Claims

1. A method for reducing rotor-stator interaction tones in an annular duct surrounding a plurality of circumferentially spaced rotor blades and a plurality of circumferentially spaced stator vanes axially spaced apart from the rotor blades, the annular duct including an inlet for receiving air and an outlet for discharging at least a portion of the air compressed by the rotor blades, comprising a step of proving a controlled air blowing system for blowing an air flow in a direction opposite to the rotation of blade-wakes into the annular duct between the rotor blades and the stator vanes to impart an opposite rotational momentum with respect to the air compressed by the rotor blades, thereby reducing the strength of a spinning mode generated by a symmetrical pattern of the blade rotation-wakes of the compressed air.

2. A method as claimed in claim 1 wherein the air flow has a temperature higher than a temperature of the compressed air to increase a local sound speed.

3. A method as claimed in claim 2 wherein the higher temperature air flow is blown to the annular duct to make a local Mach number smaller than 1.1.

4. A method as claimed in claim 1 wherein the air flow is asymmetrically blown into the annular duct to destroy the symmetrical blade rotation-wake pattern, thereby preventing the generation of the spinning mode.

5. A method as claimed in claim 1 comprising a step of providing a plurality of nozzles in an outer wall of the annular duct to blow the air flow penetrating a radial distance ranging from 5% to 20% of a length from a tip of the rotor blades to a rotational axis of the rotor blades.

6. A gas turbine engine fan assembly comprising:

a plurality of circumferentially spaced rotor blades;

a plurality of circumferentially spaced stator vanes axially spaced apart from the rotor blades;

an annular duct surrounding the rotor blades and stator vanes, and having an inlet for receiving air and an outlet for discharging at least a portion of the air upon compression by the blades; and

means for blowing an air flow in a direction opposite to the rotation of blade-wakes into the annular duct between the rotor blades and the stator vanes to impart an opposite rotational momentum with respect to the air compressed by the rotor blades, thereby reducing the strength of a spinning mode generated by a symmetrical pattern of the blade rotation-wakes of the compressed air.

7. A fan assembly as claimed in claim 6 wherein means for blowing an air flow is adapted for blowing an air flow having a temperature higher than a temperature of the compressed air to increase a local sound speed.

8. A fan assembly as claimed in claim 6 wherein the means include a plurality of nozzles in an outer wall of the annular duct, the nozzles being connected to a compressed air source of the gas turbine engine for controllably blowing the air flow.

9. A fan assembly as claimed in claim 6 wherein the nozzles are circumferentially spaced apart in an asymmetrical pattern to blow the air flow asymmetrically into the annular duct to destroy the symmetrical blade rotation-wake pattern, thereby preventing the generation of the spinning mode.

10. A fan assembly as claimed in claim 6 wherein each of the nozzles is oriented in a transverse cross section angularly with respect to a diametrical line of the annular duct passing the nozzle so that the air flow is adapted to controllably penetrate a radial distance ranging from 5% to 20% of a length of a fan radius when the means are in operation.

11. A fan assembly as claimed in claim 6 wherein at least a number of the nozzles are axially spaced apart from one another and form a row extending axially from the rotor blades to the stator vanes.

12. A fan assembly as claimed in claim 6 wherein the nozzles are arranged in an array including circumferentially spaced rows extending between the rotor blades and the stator vanes, each row including a number of the nozzles axially spaced apart from one another.

13. A fan assembly as claimed in claim 6 wherein the nozzle rows are asymmetrically located along the circumference of the outer wall of the annular duct.

14. A fan assembly as claimed in claim 6 wherein the nozzle array includes at least one row oriented angularly with respect to an axial direction of the fan assembly.