Auxiliary power source in an unducted fan gas turbine engine

• US 4,936,748 A
• Filed: 11/28/1988
• Issued: 06/26/1990
• Est. Priority Date: 11/28/1988
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Butler, Lawrence, Adamson, Arthur P.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US07/276,988
• Time in Patent Office: 575 Days
• Field of Search: 416/123, 416/171, 416/170 B, 416/129, 60/39.162, 60/226.1, 60/268
• US Class Current: 416/123
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02C 9/56 with power transmission control
• CPC Class Codes: F02K 3/072 with counter-rotating , e.g. fan rotors
• CPC Class Codes: F05D 2220/325 to drive unshrouded, high solidity propeller
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A power takeoff for an unducted fan gas turbine engine having first and second counterrotating coaxial rotors coupled respectively to first and second propellers. The rotors and propellers are oriented for rotation about a longitudinal axis of the engine. A gear is coupled to each of the rotors for rotation therewith and arranged to provide rotational motion about an axis transverse to the engine axis. A shaft is coupled to the gear for rotation about the transverse axis. Each of the propellers includes a plurality of propeller blades, each of the blades is rotatable about a corresponding blade axis, and a control is coupled to the blades for varying the pitch thereof whereby power is selectively distributed between the propellers and the power takeoff. The power takeoff may include a propeller coupled to the shaft for developing thrust substantially transverse to the engine axis and/or a pump, compressor, or generator to supply fluids or electric power to other apparatus.

Claims

1. In an unducted fan gas turbine engine including first and second coaxially disposed rotors oriented for rotation about a longitudinal engine axis, a plurality of first propeller blades coupled to the first rotor and a plurality of second propeller blades coupled to the second rotor, the propeller blades providing thrust along the longitudinal axis, apparatus for converting power from the rotors into thrust transverse to the longitudinal axis of the engine comprising:

gear means coupled to the first and second rotors for providing power transverse to the longitudinal axis; and

thrust means coupled to a said gear means for converting the transverse power into a thrust transverse to the longitudinal axis.

2. The apparatus of claim 1 wherein said thrust means comprises:

at least one rotatable shaft coupled to said gear means; and

at least a first propeller coupled to said first rotatable shaft for rotation in a plane substantially parallel to the engine longitudinal axis.

3. The apparatus of claim 2 wherein said first propeller comprises a plurality of rotatable propeller blades and including means for regulating the thrust transverse to the engine longitudinal axis.

4. The apparatus of claim 3 wherein said regulating means comprises means for varying the pitch of said propeller blades.

5. The apparatus of claim 1 wherein said gear means comprises means for providing at least one preselected gear ratio between said thrust means and the first and second rotors.

6. A power takeoff for an unducted fan gas turbine engine having first and second counterrotating coaxial rotors coupled respectively to first and second propellers, the rotors and propellers being oriented for rotation about a longitudinal axis of the engine, said power takeoff comprising:

gear means coupled to each of the rotors for rotation therewith, said gear means being arranged to provide rotational motion about an axis transverse to the engine axis; and

shaft means coupled to said gear means for rotation about said transverse axis.

7. The power takeoff of claim 6 wherein said gear means comprises at least one bevel gear, each of said first and second rotors including at least one fixedly attached gear arranged to engage said bevel gear whereby each of said rotors provides substantially the same power to said bevel gear.

8. The power takeoff of claim 6 wherein each of said propellers includes a plurality of propeller blades, each of said blades being rotatable about a corresponding blade axis, and control means coupled to said blades for varying the pitch thereof whereby power is selectively distributed between said propellers and said power takeoff.

9. The power takeoff of claim 8 wherein the pitch of said propeller blades is selectable to effect rotation of said shaft means in response to airflow over said propeller blades.

10. The power takeoff of claim 8 and including at least one propeller coupled to said shaft means for developing thrust substantially transverse to said engine axis.