Apparatus and methods for testing performance of a material for use in a jet engine

1. A miniature jet engine, comprising:

a component constructed from a material suitable for use in a corresponding component of a full-size jet engine substituted for an original component of the miniature jet engine; and

one or more sensors for reporting operational data relating to a failure mode of the component.

2. The miniature jet engine of claim 1 , wherein the component is a rotor.

3. The miniature jet engine of claim 1 , wherein the one or more sensors record one or both of temperature of exhaust gases, and revolutions per minute, during operation of the engine.

4. A method of adapting a miniature jet engine to test a material, the method comprising:

removing an original component from the miniature jet engine;

substituting a new component in place of the original component, wherein the new component is constructed from the material and wherein the new component corresponds to a component of a full-size jet engine; and

configuring the miniature jet engine with one or more sensors for reporting operational data relating to a failure mode of the new component.

5. A method of studying a failure mode of a jet engine, the method comprising:

removing an original component from a miniature jet engine;

substituting a new component in place of the original component, wherein the new component is constructed from a material used in corresponding component of a full-size jet engine;

running one or more tests on the miniature jet engine; and

in between the one or more tests, disassembling the jet engine and making a measurement relating to the failure mode on the new component.

6. The method of claim 5 , wherein the test is a cyclic test or a constant speed test.

7. The method of claim 5 , wherein the new component is a rotor.

8. The method of claim 5 , wherein the miniature jet engine has one or more components selected from a group consisting of: air intake, rotor, fan blade, combustor, housing, and compressor.

9. The method of claim 5 , wherein the full-size jet engine is a jet engine of a civil or military aircraft, and wherein the aircraft is selected from the group consisting of: helicopter, fixed-wing aircraft, and a vertical take-off and landing aircraft.

10. The method of claim 5 , wherein the test material is nickel superalloy.

11. The method of claim 10 , wherein the nickel superalloy is IN713.

12. The method of claim 5 , wherein the miniature jet engine is a functioning jet engine from a model airplane.

13. The method of claim 5 , wherein the miniature jet engine is a jet engine from an unmanned aerial vehicle.

14. The method of claim 5 , wherein the miniature jet engine is a commercially available engine.

15. The method of claim 5 , wherein the miniature jet engine has a size that is a fraction of that of a full-size jet engine, wherein the fraction is selected from the group consisting of: ⅙th, 1/10th, 1/12th, 1/16th, 1/20th, 1/24th, 1/30th, 1/36th, or 1/48 th .

16. The method of claim 5 , wherein the miniature jet engine has a rotor that is configured to rotate at between 20,000 and 165,000 revolutions per minute.

17. The method of claim 16 , wherein the rotor comprises an airfoil, and wherein the airfoil attains a temperature between about 800° F. and 1350° F. during operation of the miniature jet engine.

18. The method of claim 17 , wherein during the test on the miniature jet engine, a thermal gradient between the airfoil and the rotor shaft causes a loading that is equivalent to a loading due to a thermal gradient in the full-size jet engine.

19. The method of claim 5 , wherein the miniature jet engine comprises a rotor shaft to which a rotor is attached.

20. The method of claim 19 , wherein, during operation of the miniature jet engine, the rotor shaft attains a temperature no greater than 400° F.

21. The method of claim 5 , wherein the failure mode is selected from the group consisting of: low cycle fatigue, foreign object damage, erosion, creep, crack growth, stress corrosion, thermal mechanical fatigue, fretting, and manufacturing defects.

22. The method of claim 21 , wherein the failure mode is thermal mechanical fatigue, and wherein running one of the tests on the miniature jet engine comprises:

operating the miniature jet engine under a combination of steady state and transient operating conditions; and

obtaining a temperature profile within the miniature jet engine during each of the steady state and transient operating conditions.

23. The method of claim 21 , wherein the failure mode is low cycle fatigue, and wherein one or more of the tests on the miniature jet engine is a cyclic test.

24. The method of claim 21 , wherein the failure mode is erosion, and wherein one or more of the tests on the miniature jet engine is a constant speed test, and wherein the method further comprises:

introducing solid particles in front of an inlet of the miniature engine during the one or more tests;

interrupting the operation of the miniature engine at predetermined intervals;

disassembling and cleaning the miniature engine during the interruptions at the predetermined intervals; and

measuring during the interruptions a loss of mass or a change in geometry of the new component.

25. The method of claim 5 , wherein the failure mode is creep, and wherein running one of the tests on the miniature jet engine comprises:

operating the miniature jet engine at a constant temperature and a constant speed during the test; and

wherein the making a measurement on the new component comprises measuring a length of the new component.

26. The method of claim 25 , wherein the constant temperature is 780° C. and the constant speed is 160,000 revolutions per minute.

27. The method of claim 21 , wherein the failure mode is crack growth, and wherein one or more of the tests is a cyclic test.

28. The method of claim 27 , further comprising, before the running one or more tests, seeding the new component with a fault configured to simulate damage selected from the group consisting of: impact, corrosion, erosion, nicks, defects, and cracks.

29. The method of claim 27 , wherein the cyclic test includes a minimum speed of 38,000 revolutions per minute and a maximum speed of 123,000 revolutions per minute.