Gas turbine engine control using acoustic pyrometry

• US 8,565,999 B2
• Filed: 12/14/2010
• Issued: 10/22/2013
• Est. Priority Date: 12/14/2010
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Bunce, Richard H., Desilva, Upul P.
• Primary Examiner(s): Amin, Bhavesh V
• Application Number:
  US12/967,148
• Publication Number:
  US 20120150413A1
• Time in Patent Office: 1,043 Days
• Field of Search: None
• US Class Current: 701/100
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: G01K 11/24 of the velocity of propagation of sound

Abstract

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

Claims

1. A method operating a gas turbine engine, including determining a temperature of a working gas passing through a flow path within the gas turbine engine, the method comprising the steps of:

transmitting acoustic signals from a plurality of acoustic transmitters located at a predetermined axial location adjacent to and downstream from a last stage of a turbine section of the gas turbine engine;

receiving the acoustic signals from the acoustic transmitters at a plurality of acoustic receivers located at the predetermined axial location;

each acoustic signal comprising a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path;

determining, using a processor, a time-of-flight for the signals traveling along each of the line-of-sound paths; and

processing, via a processor, the time-of-flight for the signals traveling along the line-of-sound paths to determine a temperature in a region of the predetermined axial location.

2. The method of claim 1, including transmitting acoustic signals for determining the time-of-flight along the line-of-sound paths at a predetermined time interval between a time of transmission of each of the acoustic signals.

3. The method of claim 1, including at least one of the acoustic transmitters transmitting at least one of the acoustic signals at a frequency that is different from the frequencies of the other acoustic signals, and wherein the at least one acoustic signal is transmitted simultaneously with at least one other acoustic signal of a different frequency transmitted from another acoustic transmitter.

4. The method of claim 1, wherein the plurality of acoustic transmitters are distributed around an outer boundary of the flow path, and including processing the time-of-flight for each of the acoustic signals to determine a plurality of local temperatures for the working gas in a corresponding plurality of regions distributed in a plane extending across the flow path at the predetermined axial location.

5. The method of claim 4, wherein the plurality of regions are distributed circumferentially around an axis of the gas turbine engine extending parallel to the flow path.

6. The method of claim 5, wherein the plurality of regions are further distributed radially between the outer boundary of the flow path and the axis of the gas turbine engine.

7. The method of claim 5, including the steps of:

matching each of the regions circumferentially with a corresponding one of a plurality of combustors of the turbine engine; and

controlling a fuel/air mixture of each of the combustors with reference to the local temperature at a corresponding region.

8. The method of claim 4, wherein the plurality of regions distributed in the plane extending across the flow path comprise a first set of point temperature measurements within the flow path, and including a second set of point temperature measurements located at different locations within the flow path than locations of the first set of point temperature measurements, and including the steps of:

monitoring the temperatures in the flow path at the first set of point temperature measurements and controlling an operating parameter of the gas turbine engine based on the temperatures at the first set of point temperature measurements during a first operating condition of the gas turbine engine; and

monitoring the temperatures in the flow path at the second set of point temperature measurements and controlling the operating parameter of the gas turbine engine based on the temperatures at the second set of point temperature measurements during a second operating condition of the gas turbine engine different from the first operating condition.

9. The method of claim 8, wherein the first operating condition of the gas turbine engine comprises a base load operation of the gas turbine engine, and the second operation condition of the gas turbine engine comprises a partial load operation of the gas turbine engine.

10. The method of claim 4, further including processing the time-of-flight for each of the acoustic signals to determine a bulk temperature comprising an average temperature for the working gas at the plane extending across the flow path at the predetermined axial location.

11. The method of claim 4, wherein each acoustic transmitter and acoustic receiver defines a transceiver, and the transceivers are circumferentially spaced around the outer boundary of the flow path, and including an inner boundary located radially inwardly from an outer boundary, and at least some of the line-of-sound paths comprise first and second path segments, the first path segment extending from a transmitting transceiver to the inner boundary and the second path segment extending from the inner boundary to a receiving transceiver.

12. The method of claim 1, including providing a distance measuring device and determining a distance measurement from at least one of the acoustic transmitters to at least one of the acoustic receivers, and correcting the determination of the temperature in the region of the predetermined axial location where the at least two line-of-sound paths intersect with reference to the distance measurement.

13. The method of claim 1, including measuring a background noise level at the predetermined axial location and adjusting an attenuation level for filtering the acoustic signals received by the acoustic receivers with reference to the background noise level during processing of the time-of-flight signals to determine the temperature in the region of the predetermined axial location where the at least two line-of-sound paths intersect.

14. The method of claim 1, including obtaining a wall temperature measurement at the predetermined axial location, and inputting the wall temperature measurement to provide a boundary layer temperature gradient during processing of the time-of-flight signals to determine the temperature in the region of the predetermined axial location where the at least two line-of-sound paths intersect.

15. The method of claim 1, wherein at least two of the line-of-sound paths intersect within the flow path, and comparing the temperatures determined for each of the at least two line-of-sound paths to verify an accuracy of the temperature provided by each of the at least two line-of-sound paths.

16. A gas turbine engine including an apparatus for controlling operation of the gas turbine engine comprising:

a plurality of acoustic transmitters located circumferentially on a boundary structure defining a flow path for a working gas passing through the gas turbine engine, the plurality of acoustic transmitters located at a predetermined axial location adjacent to and downstream from a turbine section of the gas turbine engine;

a plurality of acoustic receivers located circumferentially around the boundary structure defining the flow path at the predetermined axial location;

a plurality of line-of-sound paths defined by acoustic signals, each acoustic signal transmitted from an acoustic transmitter and received by an acoustic receiver for a respective line-of-sound path; and

a controller configured to determine a time-of-flight for the acoustic signals traveling along each of the line-of-sound paths, and the controller being configured to process a measured time-of-flight for the signals traveling along the line-of-sound paths to determine a local temperature in each of a plurality of locations located circumferentially around the flow path at the predetermined axial location.

17. The gas turbine engine of claim 16, wherein the gas turbine engine comprises a combustion section, and the controller being configured to calculate a bulk exhaust gas temperature of the working gas at the predetermined axial location, the bulk temperature comprising an average of the temperatures at the plurality of locations, and the controller being configured to control a firing temperature in the combustion section with reference to the bulk temperature.

18. The gas turbine engine of claim 16, wherein each acoustic transmitter and acoustic receiver defines a transceiver, and the transceivers are circumferentially spaced around a circumferentially outer boundary of the boundary structure.

19. The gas turbine engine of claim 18, wherein the boundary structure comprises an inner boundary and at least some of the line-of-sound paths comprise first and second path segments, the first path segment extending from a transmitting transceiver to the inner boundary and the second path segment extending from the diffuser to a receiving transceiver.

20. The gas turbine engine of claim 16, wherein the boundary structure comprises an inner boundary located radially inwardly from an outer boundary of the boundary structure, and one of the acoustic transmitters and the acoustic receivers being located on one of the inner boundary and the outer boundary, and the other of the acoustic transmitters and the acoustic receivers being located on the other of the inner boundary and the outer boundary.