Gas turbine engine starting

• US 5,253,470 A
• Filed: 07/22/1992
• Issued: 10/19/1993
• Est. Priority Date: 10/16/1991
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Newton, Arnold C.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): WICKER, WILLIAM
• Application Number:
  US07/916,669
• Time in Patent Office: 454 Days
• Field of Search: 60/39.141, 60/39.142, 60/730, 60/736, 60/39.83, 60/39.08, 184/6.3, 184/6.11
• US Class Current: 60/39.08
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/272 generated by cartridges

Abstract

A ducted fan gas turbine engine (10) is provided with an electric motor starter unit (16). The oil lubrication system of the engine (10) is so arranged that during engine starting, the heat generated by the starter unit (16) is used to heat up the oil in the system. This reduces the viscosity of the oil, thereby facilitating easy engine starting under very cold conditions.

Claims

1. A gas turbine engine provided with an electric starter unit, said starter unit being adapted to provide rotation by direct drive of at least one of the rotatable parts of said gas turbine engine to facilitate engine starting, said gas turbine engine having an oil-based lubrication system, means being provided to place the oil in said lubrication system in heat exchange relationship with said electric motor starter unit, at least during engine starting, to provide an increase in temperature, end consequent decrease in viscosity, of said lubrication system oil.

2. A gas turbine engine as claimed in claim 1 wherein said engine includes compressor and turbine sections drivingly interconnected by shaft means, said starter unit being adapted to drive said shaft means during engine starting.

3. A gas turbine engine as claimed in claim 1 wherein said oil-based lubrication system includes a heat exchanger, said heat exchanger being adapted to place oil contained within said lubrication system in heat exchange relationship with fuel operationally passing through the fuel system of said gas turbine engine.

4. A gas turbine engine as claimed in claim 1 wherein means are provided to by-pass at least part of the oil directed to said starter unit for heat exchange therewith during the normal running of said engine.

5. A gas turbine engine as claimed in claim 1 wherein said starter unit is additionally adapted to function as an electric generator during normal engine running.

6. A gas turbine engine as claimed in claim 1 wherein said engine is a ducted fan gas turbine engine.