William M Farrell

US Patent:

51505673, Sep 29, 1992

Filed:

Dec 3, 1990

Appl. No.:

7/620956

Inventors:

William M. Farrell - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02G 300

US Classification:

60 3902

Abstract:

A powerplant comprising a first compressor for producing a downstream axial flow, a second compressor positioned downstream of the first compressor and combustor positioned downstream of the second compressor. A first turbine is positioned downstream of the combustor and the first turbine is drivingly connected to the second compressor through a first shaft. A second turbine is positioned downstream of the first turbine and the second turbine is drivingly connected to the first compressor through a second shaft. The powerplant is connected to a load which is primarily rotary as opposed to a downstream axial thrust and the load is coupled to the second shaft. Further the invention includes a method of converting an aircraft turbofan engine having a fan, and a compressor for producing a downstream flow adjacent the fan, to a non-aeronautical application comprising the steps of removing a fan from a shaft of the engine and attaching a connection for attaching a load to the shaft from which the fan is removed.

US Patent:

51600803, Nov 3, 1992

Filed:

Oct 1, 1990

Appl. No.:

7/590723

Inventors:

William R. Hines - Montgomery OH
William M. Farrell - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 600

US Classification:

60 3904

Abstract:

A method of operating a gas turbine engine includes providing combustion gases to turbine means, and choking flow of the combustion gases for increasing shaft horsepower in an output shaft while reducing thermal efficiency of the gas turbine engine. The method may also include the step of supercharging the turbine means for further increasing output shaft horsepower. In accordance with an exemplary embodiment, a gas turbine engine effective for carrying out the method is disclosed. The engine includes an output shaft, compression means, combustion means, turbine means, and diffusion means for diffusing combustion gases discharged from the turbine means for obtaining choked flow for increasing shaft horsepower and reducing thermal efficiency. The compression means is effective for supercharging the turbine means at a predetermined speed of the output shaft for providing increased output shaft horsepower.

US Patent:

47856211, Nov 22, 1988

Filed:

May 28, 1987

Appl. No.:

7/055213

Inventors:

Edgar D. Alderson - Ballston Spa NY
William M. Farrell - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 328

US Classification:

60 3912

Abstract:

In a coal gasification plant there is a requirement for supplying oxygen to the coal gasifier in order to produce coal gas fuel. An oxygen plant will produce oxygen and nitrogen from an input supply of compressed air. In the presence of a fired gas turbine which is supplied with coal gas fuel, the waste heat from the fired gas turbine may be used to heat compressed air for driving an air cycle turbine. The air cycle turbine in turn drives an air cycle compressor for producing air to the oxygen plant. The nitrogen gas by-product from the oxygen plant is injected into the air cycle for disposal through the air turbine.

US Patent:

55534481, Sep 10, 1996

Filed:

Sep 6, 1994

Appl. No.:

8/301363

Inventors:

William M. Farrell - Cincinnati OH
Gary L. Leonard - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 106

US Classification:

60 39161

Abstract:

A gas turbine engine having improved output horsepower and a method of achieving it. The engine has, in order, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine and a low pressure turbine. The high pressure turbine is drivingly connected to both compressors with a speed reducing gear box therebetween. An intercooler between the compressors reduces the horsepower requirement of the high pressure compressor. Flow from the combustor is sufficiently heated to enable the high pressure turbine to drive both compressors with the output horsepower of the low pressure turbine devoted to the engine load.

US Patent:

54191122, May 30, 1995

Filed:

Oct 25, 1991

Appl. No.:

7/783030

Inventors:

William M. Farrell - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 600

US Classification:

60 3915

Abstract:

A double ender powerplant including a first engine having a compressor for producing a downstream axial flow, a combustor, a turbine coupled to the compressor through a shaft, and means for attaching a load coupled to the shaft adjacent and downstream from the turbine; a second engine having a compressor for producing a downstream axial flow, a combustor, a turbine coupled to the compressor through a shaft, and means for attaching a load coupled to the shaft adjacent and upstream from the compressor; and, a generator coupled to each of the attachment means of the first and second engines.

US Patent:

59116790, Jun 15, 1999

Filed:

Dec 31, 1996

Appl. No.:

8/775699

Inventors:

William M. Farrell - Cincinnati OH
Padmakar M. Niskode - Cincinnati OH
Michael W. Horner - West Chester OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 7042

US Classification:

60 39183

Abstract:

A cospander for extending the high efficiency range of a turbine engine is described. A cospander, in one aspect, is a turbomachinery device including at least one stage wherein stator vane and rotor blade rows are continuously variable to an extent that each stage can be operated in compression, expansion, or null modes depending on the blade and vane angles at any specific operating point. Such a device placed ahead or within a typical compressor has the effect of reducing, increasing, or maintaining the through flow of the primary working fluid. Such flow variation control can be used to achieve the desired overall turbomachinery thermal efficiency improvements over a wider operating range than is otherwise possible. In one specific embodiment, for example, the cospander includes a variable stator vane and a variable pitch rotor blade in series flow relationship.

US Patent:

47856343, Nov 22, 1988

Filed:

May 28, 1987

Appl. No.:

7/055398

Inventors:

Edgar D. Alderson - Ballston Spa NY
William M. Farrell - Cincinnati OH

Assignee:

General Electic Company - Schenectady NY

International Classification:

F02C 104

US Classification:

60682

Abstract:

The use of hot gas generators which produce corrosive or abrasive products of combustion have precluded the use of gas turbines in a direct flow path of the combustion products. It is preferable to utilize non-contact gas to gas heat exchangers in order to transfer heat from a hot gas stream to a working fluid. A first heat exchanger connected to a gas furnace is used to raise the temperature of an air turbine inlet gas. A second heat exchanger is used to raise the temperature (prewarm) of compressor discharge air to the air turbine air inlet, the second heat exchanger connected to the air turbine exhaust. A third heat exchanger preheats the air input into a furnace.