ACOUSTIC MEASUREMENT SYSTEM INCORPORATING A TEMPERATURE CONTROLLED WAVEGUIDE

• US 20170016396A1
• Filed: 07/16/2015
• Published: 01/19/2017
• Est. Priority Date: 07/16/2015
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: DeSilva, Upul P., Claussen, Heiko
• Granted Patent: US 9,683,901 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 17/085 to temperature
• CPC Class Codes: F02C 7/00 Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants controlling F02C9/00
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/0831 indirectly, at the exhaust
• CPC Class Codes: F05D 2270/14 to control thermoacoustic behaviour in the combustion chambers
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: F05D 2270/333 Noise or sound levels
• CPC Class Codes: F05D 2300/133 Titanium
• CPC Class Codes: F05D 2300/177 Ni - Si alloys
• CPC Class Codes: F23N 2241/20 Gas turbines
• CPC Class Codes: F23N 5/16 using noise-sensitive detectors
• CPC Class Codes: G01K 11/22 using measurement of acoustic effects
• CPC Class Codes: G01K 11/24 of the velocity of propagation of sound
• CPC Class Codes: G01K 13/02 for measuring temperature of moving fluids or granular materials capable of flow
• CPC Class Codes: G01K 13/024 of moving gases
• CPC Class Codes: G01S 11/14 using ultrasonic, sonic, or infrasonic waves

Abstract

For a gas turbine engine (10), a method and apparatus for determining temperature of combustion gas in a flow path (17) of the engine. In one embodiment a waveguide (30) includes a cavity (36) with a first waveguide end (32) including a barrier layer (58) which may be a membrane. With the first end positioned to inject an acoustic signal into the flow path, the barrier layer (58) isolates the cavity from combustion gas. Acoustic instrumentation positioned along the surface (38i) of a wall (38) of the waveguide provides generation and propagation of acoustic signals into the flow path for detection and measurement after reflection back into the cavity. The wall may include sections of two different materials, one material having a higher melting temperature than the other, or one material having greater electrically isolating properties than the other section.

Claims

1. A measurement system for combustion gas in a gas turbine engine based on propagation of an acoustic signal while the gas passes through a measurement region in the engine, the system comprising:

a waveguide having first and second ends and a cavity extending between the first and second ends of the waveguide, the first end configured to adjoin the flow path for injection of the acoustic signal into the measurement region; and

an acoustically transmissive physical barrier positioned between a portion of the waveguide and the measurement region to prevent movement of the combustion gas from the measurement region into the waveguide while permitting transmission of the acoustic signal from the waveguide into the measurement region.

2. The system of claim 1 wherein the acoustically transmissive physical barrier is a membrane positioned to seal the cavity, the system including at least one device for transmitting or receiving the acoustic signal along a wall of the waveguide.

3. The system of claim 2 wherein the at least one device is a transmitter positioned to generate the acoustic signal for propagation into the measurement region.

4. The system of claim 2 wherein the at least one device is a transmitter positioned to generate the acoustic signal for propagation into the measurement region, the system further including a receiver positioned along a wall of the waveguide to monitor return of the acoustic signal after reflection from the measurement region.

5. The system of claim 1 further comprising a cooling arrangement configured to control an operating temperature of the waveguide.

6. The system of claim 5 wherein the cooling arrangement further comprises an inlet port and an outlet port extending through a wall defining the cavity to direct cooling fluid through the cavity.

7. The system of claim 6 wherein the inlet port is configured to direct at least a portion of the cooling fluid onto the acoustically transmissive barrier.

8. The system of claim 6 wherein the inlet port is positioned closer to the waveguide first end than to the waveguide second end and the outlet port is positioned between the inlet port and the waveguide second end, causing the fluid to travel in a direction away from the first end and toward the second end.

9. The system of claim 5 further comprising a wall surrounding the cavity and wherein the cooling arrangement comprises a channel formed along the wall to direct cooling fluid for controlling the operating temperature of the waveguide.

10. The system of claim 9, further comprising a series of ports extending from the channel through the wall to the cavity to provide circulation of cooling fluid through the cavity.

11. The system of claim 1 further comprising a wall surrounding the cavity, the wall comprising a first section formed of a first material extending from a transition region to the first end and a second section formed of a second material extending from the transition region to the second end, the first material having a higher melting temperature than the second material of the second section.

12. The system of claim 1 further comprising a wall surrounding the cavity, the wall comprising a first section formed of a first material extending from a transition region to the first end and a second section formed of a second material extending from the transition region to the second end, the second material having greater electrically isolating properties than the first material.

13. A gas turbine engine including an apparatus for controlling operation based on propagation of an acoustic signal while the gas passes through a measurement region a measurement region in the engine by determining time of flight information for an acoustic signal propagating through the measurement region, the engine comprising:

a combustor section;

a turbine section along which a flow path extends from the combustor section;

a waveguide having first and second ends, with the first end adjoining the measurement region to enable injection of the acoustic signal into the flow path while the waveguide remains isolated from flow of the combustion gas therein, the waveguide including a barrier layer across the first end; and

acoustic instrumentation providing the functions of an acoustic transmitter and a receiver positioned along an interior wall of the waveguide to generate the acoustic signal and to sense receipt of the acoustic signal after reflection from the measurement region.

14. The gas turbine engine of claim 13 wherein the barrier layer includes a membrane comprising titanium or a nickel alloy.

15. The gas turbine engine of claim 13 including a wall surrounding a cavity, the wall comprising a first section formed of a first material extending from a transition region to the first end and a second section formed of a second material extending from the transition region to the second end, the first material having a higher melting temperature than the second material of the second section.

16. The gas turbine engine of claim 13 including a wall surrounding a cavity, the wall comprising a first section formed of a first material extending from a transition region to the first end and a second section formed of a second material extending from the transition region to the second end, the second material having greater electrically isolating properties than the first material.

17. A waveguide for use in a gas turbine engine for determining time of flight information for propagation of an acoustic signal through a measurement region in a flow path carrying engine combustion gas, the waveguide comprising:

a body comprising first and second ends and a tapered cavity extending between the first and second ends, with the first end comprising an acoustically transmissive physical barrier layer so that when the first end is positioned to adjoin the flow path to inject the acoustic signal into the flow path, the cavity remains isolated from flow of the combustion gas along the flow path; and

acoustic instrumentation positioned to provide for generation of the acoustic signal and propagation of the acoustic signal into the measurement region.

18. The waveguide of claim 17 further comprising a cooling passage configured to control temperature of the acoustic instrumentation during operation of the gas turbine engine.

19. The waveguide of claim 18 wherein the cooling passage comprises an inlet port and an outlet port positioned to pass a cooling fluid through a portion of the cavity.

20. The system of claim 18 wherein the cooling passage comprises a channel formed in the body.