Differential geared engine

• US 4,251,987 A
• Filed: 08/22/1979
• Issued: 02/24/1981
• Est. Priority Date: 08/22/1979
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Adamson, Arthur P.
• Primary Examiner(s): Garrett, Robert E.
• Application Number:
  US06/068,813
• Time in Patent Office: 552 Days
• Field of Search: 60/226 R, 60/262, 60/39.75, 60/39.16 R, 60/39.16 S, 415/122 A, 415/122 R, 74/665 K, 74/665 S, 74/714, 417/405
• US Class Current: 60/805
• CPC Class Codes: F02C 3/113 with variable power transmission between rotors
• 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: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 74/19112 Aligned

Abstract

A gas turbine engine comprising a fan, a compressor and a turbine, wherein the torque requirements of the fan or compressor can be modulated, is provided with differential gearing to transmit all of the fan and compressor power requirements from the turbine. The differential gearing maintains an adjustable speed relationship between the fan and compressor with respect to the turbine depending upon the torque requirements thereof and the gear ratios within the differential gearing.

Claims

1. A gas turbine engine comprising:

a compressor, a turbine and a nozzle, the geometry of which partially defines a flow passage through the engine;

a rotatable load;

differential gearing receiving power from said turbine and transmitting power to said compressor and load; and

means for selectively varying the engine flow passage-defining geometry to modulate the torque versus speed characteristic of at least one of the pair comprising said load and said compressor and to selectively modulate the rotational speed relationship between the compressor, turbine and load, wherein said differential gear means comprises;

a first sun gear driven by said turbine at turbine rotational speed;

planet gearing engaging said first sun gear; and

a ring gear driven by said planet gearing for driving said load in rotational motion with respect to said turbine; and

wherein

said planet gearing is operatively connected to said compressor for rotationally driving said compressor with respect to said turbine.

2. The engine as recited in claim 1 wherein said planet gearing includes a plurality of first planet gears engaged with, and radially between, said first sun gear and said ring gear.

3. The engine as recited in claim 2 wherein each of said first planet gears has associated therewith a shaft which rotates at first planet gear rotational speed, all of said first planet gears being carried by a spider for further rotation, in unison, with respect to said turbine.

4. The engine as recited in claim 3 wherein said planet gearing further includes a plurality of second planet gears, one of said second planet gears being connected to each shaft for rotation with an associated first planet gear, the diameter of said second planet gears being different than that of said first planet gears, and wherein said second planet gears drivingly rotate said compressor.

5. The engine as recited in claim 2 further comprising a second sun gear rotatably driven by said second planet gears, said second sun gear, in turn, driving said compressor.

6. The engine as recited in claim 4 further comprising a compressor shaft in gear driven engagement with said second planet gears and connected to said compressor.