Leak detection, isolation and accommodation assembly for gas turbine engines

Patent metadata

Field	Value
Publication number	US-10260425-B2
Application number	US-201615147173-A
Country	US
Kind code	B2
Filing date	May 5, 2016
Priority date	May 5, 2016
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

A fuel system for a gas turbine engine includes, among other things, a plurality of components defining a plurality of localized nodes at distinct locations relative to a fuel flow path, each of the plurality of localized nodes characterized by a distinct set of failure parameters. One or more fuel sensors are configured to measure at least one fuel condition relating to flow through the fuel flow path. A fuel observation assembly is coupled to one or more engine sensors configured to measure at least one engine condition. The fuel observation assembly comprises an estimation module operable to calculate an expected condition of each of the plurality of localized nodes based upon the set of failure parameters, an observation module operable to calculate an observed condition of each of the plurality of localized nodes, the observed condition based on present values of the at least one fuel condition and the at least one engine condition, and a comparison module operable to determine an abnormality corresponding to a first one of the plurality of localized nodes based upon a comparison of the expected condition and the observed condition for each of the plurality of localized nodes.

First claim

What is claimed is:

1. A fuel system for a gas turbine engine, comprising:
a plurality of components defining a plurality of localized nodes at distinct locations relative to a fuel flow path, each of the plurality of localized nodes characterized by a distinct set of failure parameters;
one or more fuel sensors configured to measure at least one fuel condition relating to flow through the fuel flow path; and
a fuel observation assembly coupled to one or more engine sensors configured to measure at least one engine condition, the fuel observation assembly comprising:
an estimation module operable to calculate an expected condition of each of the plurality of localized nodes based upon the set of failure parameters;
an observation module operable to calculate an observed condition of each of the plurality of localized nodes, the observed condition based on present values of the at least one fuel condition and the at least one engine condition; and
a comparison module operable to determine an abnormality corresponding to a first one of the plurality of localized nodes based upon a comparison of the expected condition and each observed condition for the plurality of localized nodes.

2. The fuel system as recited in claim 1 , wherein the estimation module is operable to calculate the expected condition of each of the plurality of localized nodes based upon estimated values and observed values of the at least one fuel condition and estimated values and observed values of the at least one engine condition.

3. The fuel system as recited in claim 2 , wherein the plurality of components includes a metering valve operable to regulate flow through the fuel flow path in response to a metering signal, and the at least one fuel condition includes the metering signal.

4. The fuel system as recited in claim 3 , wherein the plurality of localized nodes are defined by at least a plurality of fuel injectors and one or more actuators in the fuel flow path.

5. The fuel system as recited in claim 2 , wherein the at least one fuel condition relates to one or more fuel boundary conditions affecting flow through the fuel flow path and one or more fuel command signals to the plurality of components, and the at least one engine condition relates to one or more engine boundary conditions.

6. The fuel system as recited in claim 5 , wherein the one or more fuel boundary conditions include a burner pressure of a combustor and a speed of a fuel pump coupled to a fuel source.

7. The fuel system as recited in claim 1 , wherein the observed condition relates to a fuel flow rate through a corresponding one of the plurality of localized nodes.

8. The fuel system as recited in claim 1 , wherein the estimation module is operable to calculate the expected condition of each of the plurality of localized nodes based upon a previous calculation of the corresponding expected condition.

9. The fuel system as recited in claim 1 , wherein the estimation module is operable to adjust the expected condition based upon a set of failure hypotheses and associated uncertainty parameters and sensitivity parameters, the set of sensitivity parameters based on a relationship between the set of failure parameters, the at least one fuel condition, and the at least one engine condition.

10. The fuel system as recited in claim 1 , wherein the abnormality is a first abnormality, the comparison module is operable to cause the expected condition to be adjusted based on the first abnormality, and is operable to determine a second, different abnormality corresponding to another one of the plurality of localized nodes in response to adjustment of the expected condition.

11. A propulsion system, comprising:
a gas turbine engine including a combustor section in flow communication with a turbine section;
a fuel system defining a plurality of localized nodes including a metering valve, the metering valve operable to meter flow between the combustor section and a fuel source in response to a metering signal, each of the plurality of localized nodes characterized by a distinct set of failure parameters; and
a fuel observation assembly coupled to the engine and the fuel system, the fuel observation assembly comprising:
an estimation module operable to calculate an expected condition of each of the plurality of localized nodes based upon: (a) at least the metering signal, (b) at least one fuel condition relating to the fuel assembly, and (c) at least one engine condition relating to the engine;
wherein the expected condition corresponds to at least one parameter of the set of failure parameters;
an observation module operable to calculate an observed condition of each of the plurality of localized nodes based on present values of the at least one fuel condition and the at least one engine condition;
and a comparison module operable to determine an abnormality corresponding to a first one of the plurality of localized nodes based upon a comparison of the expected condition and each observed condition for the plurality of localized nodes.

12. The propulsion system as recited in claim 11 , wherein the estimation module is operable to calculate the expected condition based on a first control signal to the engine and a second control signal to the fuel system, each of the first and second control signals relating to fuel flow through the fuel assembly.

13. The propulsion system as recited in claim 11 , wherein the comparison module is operable to associate the abnormality with a single parameter of the set of failure parameters.

14. The propulsion system as recited in claim 11 , wherein the set of failure parameters includes at least a leakage condition and a sensor failure condition relating to a corresponding one of the plurality of localized nodes.

15. The propulsion system as recited in claim 11 , wherein the at least one fuel condition relates to one or more boundary conditions of the fuel system and one or fuel command signals to the fuel system, and the at least one engine condition relates to one or more boundary conditions of the engine.

16. The propulsion system as recited in claim 11 , the plurality of localized nodes are defined by at least one of a fuel pump coupled to the fuel source, an actuator, the metering valve, a distribution valve coupled to fuel injectors of the combustor section, and the combustor section.

17. The propulsion system as recited in claim 11 , wherein the comparison module is operable to cause an alert to be communicated to an aircraft cockpit in response to the abnormality meeting at least one predetermined criterion.

18. The propulsion system as recited in claim 11 , wherein the comparison module is operable to calculate an estimated fuel flow through the fuel assembly based on the abnormality, and is operable to cause a flight plan of an aircraft to adjust based on the estimated fuel flow.

19. The propulsion system as recited in claim 11 , wherein the abnormality relates to a sensor failure, the comparison module is operable to estimate a present value of the one or more fuel sensors and the one or more engine sensors associated with the abnormality, and is operable to communicate the present value to an engine control system.

20. The propulsion system as recited in claim 11 , wherein the estimation module is operable to adjust the expected condition based upon a set of failure hypotheses and associated uncertainty parameters and sensitivity parameters, the set of sensitivity parameters based on a relationship between the set of failure parameters, the at

Assignees

• United Technologies Corp

Inventors

• Crowley Timothy J
• Selstad Tyler J
• Bengea Sorin
• Luppold Robert H

Classifications

• F02C9/00

  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

• F05D2220/32

  in gas turbines · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F02C7/232

  Fuel valves {(control of fuel supply by means of fuel metering valves F02C9/263)}; Draining valves or systems (valves in general F16K) · CPC title

• F02C7/236

  Fuel delivery systems comprising two or more pumps · CPC title