William L Hines

US Patent:

6412269, Jul 2, 2002

Filed:

May 22, 2000

Appl. No.:

09/575276

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 300

US Classification:

60 3902

Abstract:

Gas turbine engines working on an inverted Brayton cycle (IBC) which provides increased power output at a same fuel flow as is currently used in some other known cycles (e. g. , air bottoming cycle) are described. In one embodiment, the engine includes a compressor coupled by a first shaft to a high pressure turbine. A combustor is located in the flow intermediate the compressor and high pressure turbine. A free wheeling power turbine is located downstream of the high pressure turbine, and the power turbine is coupled to a load by a second shaft. The flow from the power turbine is supplied, e. g. , via ducts, to an axial turbine coupled to an axial compressor by a third shaft. A heat exchanger is located in the flow intermediate the axial turbine and axial compressor. In operation, the working fluid (e. g. , air) is compressed by the compressor, and the compressed air is injected into the combustor which heats the air causing it to expand.

US Patent:

57750920, Jul 7, 1998

Filed:

May 6, 1997

Appl. No.:

8/851869

Inventors:

William R. Hines - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02D 313

US Classification:

60 39161

Abstract:

A simple cycle gas turbine engine which includes a variable flow booster, a small high pressure compressor, and a power turbine is described. The variable flow booster, which includes a low pressure compressor, has at least two flow paths. In one embodiment, variable bleed valves, or doors, are used to control air flow through respective booster flow paths. In one embodiment, a first flow path directs air flow around booster compressor to the core engine, and a second flow path directs air flow at least partially through the booster compressor.

US Patent:

57688842, Jun 23, 1998

Filed:

Nov 22, 1995

Appl. No.:

8/561657

Inventors:

William R. Hines - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 7143
F02C 920

US Classification:

60 39161

Abstract:

A gas turbine engine operable so that, in one embodiment, by adjusting the speed of an intercooler fan, the orientation of a variable inlet guide vane, and the orientation of a variable area turbine nozzle, the conditions at the inlet of the high pressure compressor are substantially the same for an ambient air temperature within the range of 59. degree. F. and 100. degree. F. The engine, in one embodiment, includes a low pressure compressor, a high pressure compressor, and an intercooler, including a fan, for cooling air output by the low pressure compressor and supplying the cooled air to the high pressure compressor.

US Patent:

50542796, Oct 8, 1991

Filed:

Feb 5, 1991

Appl. No.:

7/652234

Inventors:

William R. Hines - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02G 300

US Classification:

60 3905

Abstract:

A steam injected engine, including a compressor, a combustor and a turbine in series combination, with a gas flow path passing therethrough. A steam injection system is provided for adding superheated steam to the gas flow path. A water spray and mixer system sprays water into the steam injection system, whereby the water is immediately vaporized and the resultant mixture remains at superheated temperatures but a greater mass flow of steam is provided to the gas engine to thereby produce an increase in the power output from the engine at reduced thermal efficiency. This new system also provides a means for introducing external waste heat or waste steam into current engine steam piping.

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:

48934682, Jan 16, 1990

Filed:

Nov 30, 1987

Appl. No.:

7/126092

Inventors:

William R. Hines - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 330

US Classification:

60 3905

Abstract:

Method and apparatus for controlling the output emissions of a gas turbine engine provides an emissions combustor wherein the gas is burned locally and then thoroughly mixed with cooler unburned portions while propagating the resulting a very hot flame front is propagated over the whole gas stream flow. The emissions combustor serves to reduce the carbon monoxide content of the output. NOX can be eliminated by steam injection into the engine main combustor in combination with the emissions combustor. Combustion efficiency, which is reduced through the steam injection in the main combustor is recovered through the use of the emissions combustor. The emissions combustor can be placed at numerous locations, either as part of a main combustor staging, downstream of a high pressure turbine, or in a supplementary burner after a power turbine.

US Patent:

51741059, Dec 29, 1992

Filed:

Nov 9, 1990

Appl. No.:

7/610882

Inventors:

William R. Hines - Montgomery OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 600
F02G 300

US Classification:

60 3904

Abstract:

A method of operating a dual rotor gas turbine engine includes bypassing a predetermined portion of compressed airflow from a high pressure compressor to downstream of a high pressure turbine first stage nozzle, and increasing core speed of the engine to a value greater than a reference value for improving hot day lapse rate curve and output shaft horsepower. The method steps are performed at least at values of ambient air temperature greater than a first value thereof associated with a reference maximum value of output shaft horsepower, and without increasing high pressure compressor discharge air temperature beyond a maximum value thereof associated with the reference maximum value of the output shaft horsepower. The dual rotor, gas turbine engine includes a preexisting design, aircraft derivative core engine including a high pressure compressor and a high pressure turbine first stage nozzle. A portion of compressed airflow from the high pressure compressor is bypassed to a point downstream of the high pressure turbine first stage nozzle, and core speed is increased for increasing output shaft horsepower of a low pressure turbine without increasing high pressure compressor discharge air temperature beyond a maximum value thereof.

US Patent:

49495445, Aug 21, 1990

Filed:

Dec 6, 1988

Appl. No.:

7/280403

Inventors:

William R. Hines - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02K 1100

US Classification:

60728

Abstract:

A gas turbine engine having a series intercooler positioned between a first and a second compressor. The intercooler has a first fuel heating system which has a heated fuel outlet and the heated fuel outlet is coupled to a combuston region of the engine. The intercooler also has a second feedwater intercooler stage which heats feedwater and the heated feedwater is input into a turbine exhaust heat exchanger. At least one turbine is positioned downstream of the combustor region and the turbine exhaust heat exchanger is downstream of the turbine. The intercooler may also include the first fuel heating system having the heated fuel outlet coupled to the combustor region and a second intercooler stage having a water input port.