Method of increasing engine temperature limit margins

• US 6,681,558 B2
• Filed: 03/26/2001
• Issued: 01/27/2004
• Est. Priority Date: 03/26/2001
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Orlando, Robert Joseph, Cooker, Paul
• Primary Examiner(s): Gartenberg, Ehud
• Application Number:
  US09/817,884
• Publication Number:
  US 20020134070A1
• Time in Patent Office: 1,037 Days
• Field of Search: 602/04, 602/33, 602/42, 602/35, 602/39
• US Class Current: 60/204
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• 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: F02K 1/06 Varying effective area of jet pipe or nozzle by using fluid jets to influence the jet flow F02K1/30
• CPC Class Codes: F05D 2270/11 to prolong engine life

Abstract

A method of extending a useful serviceable life of a gas turbine engine by increasing a limiting exhaust gas temperature margin degraded by engine use without replacing engine hardware. The method includes adjusting at least one engine parameter selected from a first group of engine parameters including a nozzle area and a rotor speed.

Claims

1. A method of extending a useful serviceable life of a gas turbine engine by increasing a limiting gas temperature margin degraded by engine use without replacing engine hardware, said method comprising adjusting at least one engine parameter selected from a first group of engine parameters including a nozzle area and a rotor speed.

2. A method as set forth in claim 1 wherein the first group of engine parameters includes a fan exhaust nozzle area, a core exhaust nozzle area, a high pressure turbine inlet area and a low pressure turbine inlet area.

3. A method a set forth in claim 1 wherein the first group of engine parameters includes a fan speed.

4. A method as set forth in claim 1 wherein the nozzle area is adjusted by pivoting at least a portion of a corresponding nozzle.

5. A method as set forth in claim 1 wherein the nozzle area is adjusted by installing an insert in a corresponding nozzle.

6. A method as set forth in claim 1 wherein the nozzle area is adjusted by removing an insert from a corresponding nozzle.

7. A method as set forth in claim 1 wherein the nozzle area is adjusted by removing an ablatable material from a corresponding nozzle.

8. A method as set forth in claim 1 wherein the limiting gas temperature margin is a high pressure turbine exhaust gas temperature margin.

9. A method as set forth in claim 1 further comprising assessing an affect adjusting said engine has on at least one engine parameter selected from a second group of engine parameters including a total net engine thrust, a low pressure turbine inlet temperature, a booster stall margin, a high pressure compressor stall margin, a high pressure turbine inlet temperature, a high pressure rotor speed, a high pressure compressor exit temperature, and a specific fuel consumption.

10. A method as set forth in claim 9 wherein assessing the affect the adjusting step has on the parameter selected from said second group of engine parameters includes:

mathematically modeling engine performance to calculate an anticipated affect adjusting the parameter in said first group will have on the parameter in said second group; and

selecting an amount to adjust the parameter in said first group based on said anticipated affect.

11. A method as set forth in claim 10 further comprising:

monitoring at least one engine parameter selected from a third group of engine parameters including a fan speed, a compressor inlet pressure, a compressor outlet pressure, and a compressor outlet temperature; and

adjusting the mathematically modeled engine performance to account for the monitored engine parameter.

12. A method as set forth in claim 11 further comprising:

running the engine after adjusting the parameter selected from the first group;

monitoring the parameter selected from the third group;

re-adjusting the mathematically modeled engine performance to account for the monitored parameter; and

re-selecting the amount to adjust the parameter in said first group based on the anticipated affect provided by the re-adjusted modeled engine.

13. A method as set forth in claim 10 further comprising adjusting the mathematically modeled engine performance to account for assumed variations in engine parameters caused by engine use.

14. A method as set forth in claim 10 further comprising:

iteratively calculating the anticipated affect adjusting the parameter in said first group will have on the parameter in said second group; and

optimizing the amount the parameter in said first group is adjusted based on said interative calculations.