Engine testing system and process
Disclosed are systems and methods for testing aircraft engine that are not currently associated with a functional aircraft or systems. For testing, systems on the engine being tested are connected with the reciprocating systems (e.g., engine electronic controls, main and motive fuel) on a fully functional aircraft using conduits that have been extended to lengths enabling the connection.
1. A system for operating an aircraft engine, the system comprising:
a main fuel conduit;
a first end of a main fuel conduit configured to connect into an engine fuel delivery system existing on a first aircraft;
a second end of the main fuel conduit configured to connect into an engine fuel intake on an aircraft engine being tested, the aircraft engine being tested not being associated with the first aircraft;
the main fuel conduit being elongated to interconnect the engine fuel delivery system on the first aircraft and the aircraft engine being tested;
a motive fuel conduit, the motive fuel conduit configured on a first end to be coupled into a motive fuel output included in the engine fuel delivery system on the first aircraft, the motive fuel conduit configured on a second end to be coupled to an aircraft motive fuel intake on the engine being tested; and
the main and motive fuel conduits being configured to extend between the engine on the first aircraft and the aircraft engine being tested.
2. The system of claim 1 wherein the main and motive fuel conduits are bound together along at least a portion of a length of each of the main and motive fuel conduits.
3. A system for operating an aircraft engine, the system comprising:
a fuel conduit;
a first end of the fuel conduit configured to connect into an engine fuel delivery system existing on a first aircraft;
a second end of the fuel conduit configured to connect into an engine fuel intake on an aircraft engine being tested, the aircraft engine being tested not being associated with the first aircraft;
the conduit being elongated to interconnect the engine fuel delivery system on the first aircraft and the aircraft engine being tested;
an electrical engine control line having first and second ends;
the first end of the electrical engine control line being configured for receipt into an onboard aircraft electronic control system on the first aircraft;
the second end of the electrical engine control line being configured for receipt into a local engine control system on the engine being tested; and
a length of the electrical control line being extended to reach between the first aircraft and the engine being tested.
4. The system of claim 3 wherein the fuel conduit and electrical control lines have substantially equal lengths.
5. The system of claim 3 wherein the fuel conduit and electrical control lines are included in a kit.
6. Method of testing an aircraft engine, an engine subject to test existing in an environment lacking full functional support from at least one onboard aircraft system, the method comprising:
connecting at least one local engine system on the engine to be tested with at least one functional reciprocating system on a master aircraft;
operating the engine using the at least one functional reciprocating system;
accomplishing the connecting step by extending a conduit from the local engine system to the functional reciprocating system on the master aircraft; and
selecting a fuel delivery system as the functional reciprocating system, and a fuel receiving system as the local engine system; and
selecting a main fuel supply system as the fuel delivery system, and a main fuel receiving system as the fuel receiving system.
7. The method of claim 6 comprising:
selecting a motive fuel supply system as the fuel delivery system, and a motive fuel supply receiving system as the fuel receiving system.
8. The method of claim 6 comprising:
selecting an onboard electronic engine control arrangement and main and motive fuel delivery systems as the at least one functional reciprocating system on a master aircraft;
connecting the onboard electronic engine control arrangement on the master aircraft with a local electronic control system on the engine to be tested; and
connecting the main and motive fuel delivery systems on the master aircraft into main and motive fuel receiving systems on the engine to be tested.
9. A system for testing an aircraft engine, the system comprising:
a main fuel conduit and a motive fuel conduit;
a first end of both the main and motive fuel conduits configured to connect into an engine fuel delivery system existing on a first aircraft;
a second end of the main fuel and motive fuel conduits configured to connect into an engine fuel intake on an aircraft engine being tested, the aircraft engine being tested not being associated with the first aircraft;
the main and motive fuel conduits being elongated to interconnect the engine fuel delivery system on the first aircraft and the engine fuel intake on the aircraft engine being tested;
a first electrical engine control line having first and second ends;
the first end of the first electrical engine control line being configured for receipt into an onboard aircraft electronic control system on the first aircraft;
the second end of the first electrical engine control line being configured for receipt into a local engine control system on the engine being tested; and
a length of the first electrical engine control line being extended to reach between the first aircraft and the engine being tested.
10. The system of claim 9 wherein the main and motive fuel conduits are bound together along at least a portion of a length of the conduits.
11. The system of claim 9 comprising:
an air conduit, the air conduit extending between a bleed air system on the first aircraft and an air intake on the aircraft engine being tested.
12. The system of claim 9 wherein each of the main and motive fuel conduits and the first electrical engine control line are bundled together.
13. The system of claim 9 wherein each of the main and motive fuel conduits and the electrical control line have substantially equal lengths.
14. The system of claim 9 wherein each of the main and motive fuel conduits and the electrical control line are included in a kit.
15. The system of claim 9 wherein the onboard aircraft electronic control system on the first aircraft includes a first electrical output connector and a redundant electrical output connector and the local engine control system on the second aircraft includes a first electrical input connector and a redundant second electrical input connector, system further comprising:
the first end of the first electrical engine control line being configured for receipt onto the first electrical output connector on the first aircraft;
the second end of the first electrical engine control line being configured for receipt onto the first electrical input connector on the local engine control system on the second aircraft;
a second electrical engine control line having first and second ends;
the first end of the second electrical engine control line being configured for receipt onto the redundant electrical output connector on the onboard aircraft electronic control system on the first aircraft; and
the second end of the second electrical engine control line being configured for receipt onto the into the redundant second electrical input a local engine control system on the engine being tested.
16. The system of claim 15 wherein the first and second electrical control lines have substantially equal lengths.