Engine operations support systems and methods for reducing fuel flow

• US 9,091,616 B2
• Filed: 06/06/2013
• Issued: 07/28/2015
• Est. Priority Date: 06/06/2013
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Moeckly, Kevin, Ling, Richard
• Primary Examiner(s): Nguyen, Bao Long T
• Application Number:
  US13/911,779
• Publication Number:
  US 20140365036A1
• Time in Patent Office: 782 Days
• US Class Current: 1/1
• CPC Class Codes: F02C 9/00 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 Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/81 Modelling or simulation
• CPC Class Codes: F05D 2270/44 active, predictive, or anticipative
• CPC Class Codes: G01M 15/05 by combined monitoring of two or more different engine parameters
• CPC Class Codes: G05B 17/02 electric

Abstract

An operations support system is provided for an engine receiving fuel. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

Claims

1. An operations system for an engine receiving fuel, comprising:

a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars;

an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars and the engine data,

the engine-specific model unit including a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model configured to reduce the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine, wherein the fuel flow calculation module calculates the current fuel flow from the engine data using the thermodynamic model; and

a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

2. The operations system of claim 1, wherein the set point information includes one or more of inlet temperature, inlet pressure, engine load, shaft power, bleed flow, governing speeds, inlet geometry, and exit geometry.

3. The operations system of claim 1, wherein the set point information includes at least two of inlet temperature, inlet pressure, engine load, shaft power, bleed flow, governing speeds, inlet geometry, and exit geometry.

4. The operations system of claim 1, wherein the engine-specific model unit further includes a fuel flow prediction unit configured to generate a predicted fuel flow based on the set point information using the thermodynamic model.

5. The operations system of claim 1, wherein the engine-specific model unit is configured to calibrate the generation of the set point information.

6. The operations system of claim 1, wherein the engine-specific model unit is configured to calculate the set point information in real-time.

7. The operations system of claim 1, wherein the engine-specific model unit is configured to calculate the current fuel flow based on at least one of engine temperature, engine air pressure, engine air flow, engine fuel flow, and engine speed.

8. The operation system of claim 1, wherein the engine-specific model unit is configured to continuously determine the current fuel flow of the engine.

9. The operations system of claim 1, wherein the engine-specific model unit is further configured to adjust the thermodynamic model based on the scalars.

10. The operations system of claim 9, wherein the thermodynamic model is an engine-specific model.

11. The operations system of claim 10, wherein at least a portion of the scalars represent erosion within the engine.

12. The operations system of claim 1, wherein the set point module is configured to generate the set point information as at least two engine operating parameters that directly result in a minimized fuel flow in view of current engine loading.

13. An aircraft system, comprising:

an engine configured to receive fuel;

an engine control unit coupled to the engine and configured to adjust operation of the engine;

a user interface coupled to the engine control unit and configured to receive commands for the engine control unit to adjust operation of the engine; and

an operations system coupled to the user interface, the engine control unit, and the engine, the operation system comprising;

a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars;

an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars and the engine data,

the engine-specific model unit including a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine; and

a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

14. The aircraft system of claim 13, further comprising a graphical user interface coupled to the engine-specific model unit and configured to display the current fuel flow.

15. The aircraft system of claim 13, further comprising a graphical user interface coupled to the engine-specific model unit and configured to display the set point information.

16. The aircraft system of claim 13, further comprising a graphical user interface coupled to the operations system and the engine control unit, the graphical user interface configured to receive a user input to implement the set point information, the engine control unit configured to adjust the engine according to the set point information based on the user input.

17. A method for operations of an engine receiving fuel, comprising:

collecting engine data;

generating diagnostics data based on the engine data, the diagnostics data including scalars;

calculating current fuel flow from the diagnostics data using a thermodynamic model based on component maps associated with the engine;

storing the current fuel flow; and

calculating set point information for the engine using the thermodynamic model configured to reduce the current flow to the engine.

18. The method of claim 17, further comprising adjusting the engine based on the set point information.

19. The method of claim 18, further comprising generating predicted fuel flow based on the set point information.