Turbine engine operational testing

Patent metadata

Field	Value
Publication number	US-12305519-B2
Application number	US-202117405136-A
Country	US
Kind code	B2
Filing date	Aug 18, 2021
Priority date	Dec 20, 2017
Publication date	May 20, 2025
Grant date	May 20, 2025

Abstract

Systems and methods for conditionally performing engine operational tests for a turbine engine are provided. A system comprising at least one processor can be configured to obtain sensor data associated with at least one sensor for a turbine engine. The sensor data identifies a current fuel flow associated with the turbine engine. The system can determine a predicted fuel flow of the turbine engine based at least in part on the current fuel flow and a fuel flow reduction associated with an engine operational test. The system can compare the predicted fuel flow to at least one threshold. The system can selectively initiate the engine operational test based on comparing the predicted fuel flow to the at least one threshold.

First claim

What is claimed is:

1. A system, comprising:
one or more sensors configured to generate sensor data including one or more engine parameters of a turbine engine; and
one or more processors configured to:
determine a current fuel flow of the turbine engine;
determine a predicted fuel flow of the turbine engine based on activation of a flow reduction valve of a fuel control system associated with the turbine engine;
verify whether the predicted fuel flow satisfies at least one criteria associated with lean blowout of a combustor of the turbine engine;
in response to verifying that the predicted fuel flow satisfies the at least one criteria associated with the lean blowout of the combustor of the turbine engine, activate the reduction valve of the fuel control system in response to the predicted fuel flow satisfying the at least one criteria; and
in response to verifying that the predicted fuel flow fails to satisfy the at least one criteria associated with the lean blowout of the combustor of the turbine engine, skip activation of the reduction valve.

2. The system of claim 1 , wherein the one or more processors are configured to:
generate an identifier that the fuel control system was not tested in response to the predicted fuel flow not satisfying the at least one criteria.

3. The system of claim 1 , wherein:
the at least one criteria includes a plurality of thresholds corresponding to a plurality of different engine parameter values;
verifying whether the predicted fuel flow satisfies the at least one criteria comprises comparing the predicted fuel flow to a first threshold of the plurality of thresholds in response to a first engine parameter value of the plurality of different engine parameter values and comparing the predicted fuel flow to a second threshold of the plurality of thresholds in response to a second engine parameter value of the plurality of different engine parameter values.

4. The system of claim 1 , wherein:
the one or more processors are configured to obtain sensor data including a plurality of engine parameters of the one or more engine parameters;
the current fuel flow is represented by a first engine parameter of the one or more engine parameters;
the plurality of engine parameters comprises at least one additional engine parameter of the one or more engine parameters representing a fuel split ratio to two or more fuel nozzles, a fuel temperature, an engine core speed, or a high pressure compressor discharge pressure; and
determining the predicted fuel flow of the turbine engine is based at least in part on the at least one additional engine parameter.

5. The system of claim 1 , wherein the one or more processors are configured to:
activate the reduction valve to reduce a fuel flow rate associated with the turbine engine over a range of fuel metering valve positions.

6. The system of claim 1 , further comprising:
a thrust control malfunction accommodation (TCMA) system including the flow reduction valve.

7. The system of claim 1 , further comprising:
one or more aerial vehicles including the one or more sensors and the one or more processors.

8. The system of claim 1 , further comprising a non-transitory computer-readable medium storing computer instructions, that when executed by the one or more processors, cause the one or more processors to perform operations, the operations comprising:
determining the current fuel flow associated with the turbine engine;
inputting the current fuel flow into one or more models to determine the predicted fuel flow of the turbine engine;
determining if the predicted fuel flow satisfies at least one threshold criterion of the at least one criteria associated with a control malfunction system of the turbine engine; and
testing the control malfunction system if the predicted fuel flow satisfies the at least one threshold criterion.

9. The system of claim 8 , wherein the operations further comprise:
generating an identifier that a test of the control malfunction system was skipped if the predicted fuel flow does not satisfy the at least one threshold criterion.

10. The system of claim 8 , wherein:
the at least one threshold criterion includes a minimum fuel flow for a lean blowout margin; and
determining if the predicted fuel flow satisfies the at least one threshold criterion comprises determining whether the predicted fuel flow is at or above the minimum fuel flow.

11. The system of claim 8 , wherein:
the at least one threshold criterion includes a plurality of thresholds corresponding to a plurality of different engine parameter values; and
determining if the predicted fuel flow satisfies the at least one threshold criterion comprises comparing the predicted fuel flow to a first threshold of the plurality of thresholds in response to a first engine parameter value of the plurality of different engine parameter values and comparing the predicted fuel flow to a second threshold of the plurality of thresholds in response to a second engine parameter value of the plurality of different engine parameter values.

12. The system of claim 8 , wherein:
the operations further comprise receiving a plurality of engine parameters of the one or more engine parameters;
the current fuel flow is represented by a first engine parameter of the one or more engine parameters;
the plurality of engine parameters comprises at least one additional engine parameter of the one or more engine parameters representing a fuel split ratio to two or more fuel nozzles, a fuel temperature, an engine core speed, or a high pressure compressor discharge pressure; and
determining the predicted fuel flow of the turbine engine is based at least in part on the at least one additional engine parameter.

13. A non-transitory computer-readable medium storing computer instructions, that when executed by one or more processors, cause the one or more processors to perform operations, the operations comprising:
receiving a plurality of engine parameters from one or more sensors;
determining a current fuel flow of a turbine engine;
determining a predicted fuel flow of the turbine engine based on activation of a flow reduction valve of a fuel control system associated with the turbine engine;
verifying whether the predicted fuel flow satisfies at least one criteria associated with lean blowout of a combustor of the turbine engine;
in response to verifying that the predicted fuel flow satisfies the at least one criteria associated with the lean blowout of the combustor of the turbine engine, activating the reduction valve of the fuel control system in response to the predicted fuel flow satisfying the at least one criteria; and
in response to verifying that the predicted fuel flow fails to satisfy the at least one criteria associated with the lean blowout of the combustor of the turbine engine, skipping activation of the reduction valve.

14. The non-transitory computer readable medium of claim 13 , wherein the operations further comprise:
generating an identifier that a test of a control malfunction system was skipped if the predicted fuel flow rate does not satisfy the at least one criteria.

15. The non-transitory computer readable medium of claim 13 , wherein
the at least one criteria includes a minimum fuel flow for a lean blowout margin; and
determining if the predicted fuel flow satisfies the at least one criteria comprises determining whether the predicted fuel flow is at or above the minimum fuel flow.

16. The non-transitory computer readable medium of claim 13 , wherein:
the at least one criteria includes a plurality of th

Assignees

• Gen Electric

Inventors

• Jastrzembowski Steven James
• Zieg Thomas Edward
• Utah Jared
• Seager Jeremy
• Houpt Michael

Classifications

• F05D2270/306

  Mass flow · CPC title

• F02C9/00 Primary

  Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) · CPC title

• F05D2260/821

  Parameter estimation or prediction · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F05D2270/092

  in particular blow-out and relight · CPC title