Aircraft jet engine testing tool

• US 5,741,965 A
• Filed: 11/29/1996
• Issued: 04/21/1998
• Est. Priority Date: 11/29/1996
• Status: Expired due to Fees

• Current Assignee: Carlos M. Hernandez, Ramos, Charles
• Original Assignee: Carlos M. Hernandez, Ramos, Charles
• Inventors: Ramos, Charles, Hernandez, Carlos M.
• Primary Examiner(s): Dombroske, George M.
• Assistant Examiner(s): MCCALL, ERIC SCOTT
• Application Number:
  US08/758,483
• Time in Patent Office: 508 Days
• Field of Search: 73/66, 73/456, 73/459, 73/460, 73/487, 73/583, 73/116, 73/119 R, 73/865.3
• US Class Current: 73/112.01
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 25/36 using electric motors

Abstract

The present invention is directed towards an aircraft engine testing tool which facilitates the visual inspection of aircraft internal engine blades by permitting the automatic repositioning of the internal engine blades to an inspection orientation. The aircraft engine testing tool includes a power driver structured to selectively and in a precisely controlled manner turn internal engine and which includes a gear down assembly that produces substantial amounts of low speed torque, and a gear spline connected to the gear down assembly and structured to rotate at substantially low speeds in accordance with the low speed torque produced by the gear down assembly. A mounting plate secures the gear spline operatively within an aircraft engine gear socket such that the low speed rotation of the gear spline results in a corresponding rotation of a plurality of the internal engine gears of an aircraft engine'"'"'s constant speed drive and therefore the internal engine blades. The aircraft engine testing tool further comprises a processor unit structured to receive a power supply and provide for regulated and controlled power and directional output to the power driver, from a remote location, thereby facilitating precise control of the direction and speed of the low speed rotation of the gear spline and therefore the internal engine blades.

Claims

1. To be used to facilitate the internal inspection of an aircraft engine;

an aircraft engine testing tool comprising;

(a) a power driver structured to selectively and in a precisely controlled manner turn internal engine blades into an inspection orientation, said power driver comprising;

a gear down assembly structured to produce substantial amounts of low speed torque,

a gear spline connected with said gear down assembly and structured to rotate at substantially low speeds in accordance with said low speed torque produced by said gear down assembly,

said gear spline being structured to be drivingly disposed within an aircraft engine gear socket such that said low speed rotation thereof results in corresponding rotation of a plurality of internal engine gears of an aircraft engine'"'"'s constant speed drive and the engine blades thereof, and

mount means structured and disposed to maintain said gear spline operatively within the aircraft engine gear socket, during said low speed rotation thereof, such that said low speed torque produced by said gear down assembly is directed through said gear spline towards rotating the plurality of internal engine gears;

(b) a processor unit, said processor unit comprising;

power receiving means structured and disposed to receive power from a power source,

power supply means structured and disposed to supply power to said power driver,

output regulating means structured and disposed to regulate a power output and directional control to said gear down assembly of said power driver, and

control means structured and disposed to permit facilitated control of said output regulating means so as to regulate a direction and speed of said low speed rotation of said gear spline.

2. An aircraft engine testing tool as recited in claim 1 wherein said processor unit includes a compact housing structured to contain said output regulating means.

3. An aircraft engine testing tool as recited in claim 2 wherein said compact housing includes a substantially sealed, fluid and dust impervious configuration.

4. An aircraft engine testing tool as recited in claim 2 wherein said compact housing acts as a heat sink structured to absorb and dissipate a quantity of heat produced by said output regulating means during operation thereof.

5. An aircraft engine testing tool as recited in claim 2 wherein said power receiving means includes an external power cord connected between said power source and said output regulating means.

6. An aircraft engine testing tool as recited in claim 5 wherein said compact housing includes a power input plug structured to receive said external power cord in power receiving communication therewith.

7. An aircraft engine testing tool as recited in claim 1 wherein said power receiving means are structured to receive variable voltage power inputs.

8. An aircraft engine testing tool as recited in claim 1 wherein said power receiving means are structured to receive said power from both a 220 volt power source and a 110 volt power source.

9. An aircraft engine testing tool as recited in claim 8 wherein said processor unit further includes an input voltage selection switch.

10. An aircraft engine testing tool as recited in claim 9 wherein said input voltage selection switch includes a three position toggle switch structured to be moved between a 110 volt receiving position, an off position, and a 220 volt receiving position.

11. An aircraft engine testing tool as recited in claim 10 further including an adjustable position restrictor plate structured and disposed to permit movement of said input voltage selection switch selectively between only said 110 volt receiving position and said off position, or said 220 volt receiving position and said off position.

12. An aircraft engine testing tool as recited in claim 1 wherein said control means of said processor unit includes a remotely actuatable control unit connected with said output regulating means and including at least one directional control switch and a rotation speed control switch.

13. An aircraft engine testing tool as recited in claim 12 wherein said rotation speed control switch includes a potentiometer.

14. An aircraft engine testing tool as recited in claim 12 including two of said directional control switches, each being structured to direct rotation in an opposite direction.

15. An aircraft engine testing tool as recited in claim 14 wherein said directional control switches are momentary switches which must be actuated in order for rotating power to be supplied by said power supply means to said power driver.

16. An aircraft engine testing tool as recited in claim 12 wherein said remotely actuatable control unit is structured to be hand held.

17. An aircraft engine testing tool as recited in claim 16 wherein said remotely actuatable control unit is connected with said output regulating means by an elongate cord so as to permit facilitated actuation by a user while actually inspecting the internal engine blades.

18. An aircraft engine testing tool as recited in claim 12 wherein said remotely actuatable control unit includes a foot pedal.

19. An aircraft engine testing tool as recited in claim 1 wherein said gear down assembly includes a stepping motor structured to move in both a forward and a reverse direction.

20. An aircraft engine testing tool as recited in claim 1 further including ramping means structured and disposed to direct a controlled, gradual, ramped increase and decrease of said low speed torque produced by said gear down assembly.

21. An aircraft engine testing tool as recited in claim 1 wherein said gear down assembly is structured to produce up to approximately 1700 lbs of force.

22. An aircraft engine testing tool as recited in claim 1 wherein said gear spline is structured to be operatively connected within the aircraft engine gear socket of a JT8 style aircraft engine.

23. An aircraft engine testing tool as recited in claim 1 wherein said gear spline is structured to be operatively connected within the aircraft engine gear socket of a JT3 style aircraft engine.

24. An aircraft engine testing tool as recited in claim 1 wherein said gear spline is structured to be operatively connected into the aircraft engine gear socket disposed at a starter pad of an engine gearbox and structured to normally receive an engine starter control.

25. An aircraft engine testing tool as recited in claim 1 wherein said gear spline is structured to be operatively connected into the aircraft engine gear socket disposed at a starter pad of an engine gearbox and structured to normally receive an engine starter control, and the aircraft engine gear socket disposed at a hydraulic pump pad of the engine gearbox and structured to normally receive a hydraulic pump.

26. An aircraft engine testing tool as recited in claim 1 wherein said gear spline is structured to be operatively connected into the aircraft engine gear socket disposed at a test pad of an engine gearbox.

27. An aircraft engine testing tool as recited in claim 1 wherein said mount means of said power driver includes a mounting plate structured to be connected with a plurality of studs to which an engine component structured to normally be connected at the aircraft engine gear socket, is normally secured, thereby maintaining secure, hands free connection between said gear spline and the aircraft engine gear socket and ensuring that substantially all of said low speed torque produced by said gear down assembly is directed towards rotating said gear spline and the plurality of internal engine gears to which said gear spline is connected through the aircraft engine gear socket.

28. An aircraft engine testing tool as recited in claim 27 wherein said mounting plate is removable so as to facilitate connection between said gear spline and the aircraft engine gear socket of various engine types.

29. An aircraft engine testing tool as recited in claim 1 wherein said gear spline is removably connected with said gear down assembly so as to facilitate interchanging thereof with at least one modified gear spline structured to be drivingly disposed within said aircraft engine gear socket of varying engine types.

30. An aircraft engine testing tool as recited in claim 1 further including a gear spline adapter structured to be coupled with said gear spline so as to facilitate adaptation of said gear spline for effective connection with the aircraft engine gear socket of various engine types.