Condition based lifing of gas turbine engine components

• US 9,200,984 B2
• Filed: 10/11/2013
• Issued: 12/01/2015
• Est. Priority Date: 10/11/2013
• Status: Active Grant

• Current Assignee: Solar Turbines Incorporated (Caterpillar Incorporated)
• Original Assignee: Solar Turbines Incorporated (Caterpillar Incorporated)
• Inventors: Green, Richard James, Novaresi, Mark Alfred, Bollapragada, Sudhakar
• Primary Examiner(s): Olszewski, John R
• Assistant Examiner(s): Ziaeianmehdizadeh, Navid
• Application Number:
  US14/052,572
• Publication Number:
  US 20150105966A1
• Time in Patent Office: 781 Days
• Field of Search: None
• US Class Current: 1/1
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines
• CPC Class Codes: G05B 23/0283 Predictive maintenance, e.g. involving the monitoring of a system and, based on the monitoring results, taking decisions on the maintenance schedule of the monitored system; Estimating remaining useful life [RUL] preventive maintenance, i.e. planning maintenance according to the available resources without monitoring the system G06Q10/06
• CPC Class Codes: G07C 5/006 Indicating maintenance

Abstract

A system and methods for the condition based lifing of a gas turbine engine component is disclosed. The system and methods determine the stress and caused by fatigue and creep for each load cycle of the gas turbine engine, and use a ductility exhaustion method to combine the fatigue and creep strain rates determined from the fatigue and creep stresses to determine the remaining useful of the gas turbine engine component.

Claims

1. A method for determining when to replace a component in a gas turbine engine based on operating conditions for each load cycle of the gas turbine engine, each load cycle including one or more ramp periods where the load and operating temperatures are increased or decreased and one or more dwell periods where the load and the operating temperatures are held relatively constant, the method comprising:

recording field data of the gas turbine engine for each load cycle the component is in the gas turbine engine;

determining a life consumed of the component for each load cycle the component is in the gas turbine engine including

determining a ramp period life consumed for each ramp period using a ductility exhaustion curve for a material of the component and a ramp period stress of the load cycle determined using the field data,

determining a dwell period life consumed for each dwell period using the ductility exhaustion curve and a dwell period stress of the load cycle determined using the field data, and

summing the ramp period life consumed from each ramp period and the dwell period life consumed from each dwell period to determine a life consumed for the load cycle;

determining a total life consumed by summing the life consumed for each load cycle;

determining a remaining useful life of the component by subtracting the total life consumed from a declared service life;

comparing the remaining useful life of the component with a predetermined threshold; and

replacing the component upon reaching the predetermined threshold of the remaining useful life.

2. The method of claim 1, wherein the remaining useful life is a number of cycles and hours of life remaining operating at a rated condition.

3. The method of claim 2, wherein the declared service life is a total number of cycles and hours to exhaust the ductility at a rated condition.

4. The method of claim 1, wherein the remaining useful life for the component is determined after each load cycle of the gas turbine engine.

5. The method of claim 1, wherein the material is a superalloy.

6. The method of claim 1, wherein the material is an anisotropic material.

7. A method of service, wherein when to perform service on the gas turbine engine is determined by projecting when the component will reach a predetermined threshold of the remaining useful life determined by the method of claim 1.

8. A method for determining a remaining useful life for a component in a gas turbine engine based on operating conditions for each load cycle of the gas turbine engine, the method comprising:

recording operational data of the gas turbine engine including data for each load cycle of the gas turbine engine that the component is in the gas turbine engine, each load cycle including one or more ramp periods and one or more dwell periods, wherein the ramp periods are when the load and operating temperatures are increased or decreased and the dwell periods are when the load and the operating temperatures load are held relatively constant;

determining a ramp period stress for each ramp period of each load cycle using the operational data;

determining a ramp period strain for each ramp period from the ramp period stress using a stress-strain curve for a material of the component;

determining a ramp period strain rate for each ramp period from the ramp period strain,

determining a ramp period damage for each ramp period from the ramp period strain rate by using a ductility exhaustion curve for the material;

determining a dwell period stress for each dwell period of each load cycle using the operational data;

determining a dwell period strain for each dwell period from the dwell period stress and temperature using a creep strain curve;

determining a dwell period strain rate for each dwell period from the dwell period strain,

determining a dwell period damage for each dwell period from the dwell period strain rate by using the ductility exhaustion curve;

combining the ramp period damage for each ramp period and the dwell period damage for each dwell period to get the damage accumulated on the component during each load cycle;

determining a total damage accumulated by summing the damage accumulated for each load cycle;

determining a remaining useful life of the component by subtracting the total damage accumulated from a total available ductility; and

comparing the remaining useful life of the component with a predetermined threshold and replacing the component based upon the result of the comparison.

9. The method of claim 8, wherein the remaining useful life is a percentage of the total available ductility relative to the total damage accumulated.

10. The method of claim 9, wherein the total available ductility is determined by using creep and tensile test data.

11. The method of claim 8, wherein the remaining useful life is determined for the component and simultaneously for other gas turbine engine components.

12. A method of service, wherein when to perform service on the gas turbine engine is determined by projecting when the component will reach a predetermined threshold of the remaining useful life determined by the method of claim 8.