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.

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.

Abstract: Precompressor and pre-booster water spray injection apparatus and methods are described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with water spray injection includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. A water injection apparatus is provided for injecting water into an inlet of the high pressure compressor. The water spray injection apparatus is in flow communication with a water supply, and during engine operation, water is delivered from such supply through the injection apparatus to the inlet of the compressor.

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.

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.

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.

Abstract: The present invention is a variable area turbine nozzle for use in a turbine engine. The variable area turbine nozzle adjusts the positions of its vanes to insure efficient operation of the turbine engine. The vanes rotate about bearing assemblies that are air cooled to extend the operating life of the bearing assemblies. Each vane is cantilevered off journal bearings outside the outer casing which carry moment loads while ball bearings take all radial loads for ease of rotation. This design provides long running time of the turbine nozzles without frequent overhaul.

Abstract: A bypass flow system for a gas-side air recuperator of a gas turbine engine. Pressurized air from the compressor section of the gas turbine is caused to pass through a pair of heat exchangers arranged in parallel spaced relationship and located in the hot gas stream between the exhaust gas box and the exhaust stack of the gas turbine engine. The space between the heat exchangers comprises a bypass duct for the exhaust gases and is openable and closeable by a butterfly valve. The longitudinal edges of the bypass duct are each provided with a flow divider device extending upstream of the exhaust gas flow by a distance at least equal to the width of the bypass duct. The flow divider devices are mirror images of each other and the forwardmost longitudinal edges thereof are blunt.

Abstract: An integrated turbine and generator includes a power turbine having counter-rotating outer and inner rotor blades extending from respective outer and inner rotors. The outer and inner rotors are supported by stationary front and rear frames. At least one electrical generator includes a field core for creating magnetic poles which is disposed coaxially with an armature for generating electrical power upon relative rotation therebetween. The field core and the armature are disposed coaxially with the outer rotor and radially outwardly therefrom, with one of the field core or armature being fixedly joined to the outer rotor for rotation therewith, and the other one thereof being fixedly joined to the front and rear frames.

Abstract: An industrial gas turbine engine includes in serial flow relationship a booster compressor, core engine, power turbine, and flow channel, with the power turbine having a first shaft, joined to the booster compressor, and an output shaft, and the flow channel having an outlet. Means for selectively varying flow area of the channel outlet are provided for controlling stall margin of the booster compressor in an exemplary embodiment of the engine and method of operation. The flow area varying means is effective for providing a minimum area of the channel outlet for controlling booster compressor stall margin at least at a synchronous speed associated with powering an electrical generator. In one embodiment, the flow area varying means effects a minimum horsepower from the output shaft for allowing lock-on and lock-off of the electrical generator at synchronous speed.

Abstract: An industrial gas turbine engine includes in serial flow relationship a booster compressor, a core engine, a power turbine having a first shaft joined to the booster and an output shaft, and means for independently varying the radially outer and radially inner booster flow areas. The means for independently varying the radially inner and outer booster flow areas can include a dual panel variable booster inlet guide vane assembly having first and second variable vane portions. The vane assembly can include a first variable vane portion rotatably supported with a first vane panel extending in a cantilevered manner adjacent a second vane panel to provide a closely spaced radial clearance therebetween. Varying means can be positioned outward of a casing for independently varying the first and second vane portions. The variable vane assembly can be operable with compressor bleed means or power turbine outlet area varying means.

Abstract: The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge of the splitter into the compressor flow thereby using the total pressure Q of the flow to drive bleed flows overboard and remove particles.

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.

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.

Abstract: A powerplant comprising a compressor for producing a downstream fluid flow, a combustor downstream of the compressor, a turbine downstream of the combustor, a power turbine downstream and adjacent the turbine, and a duct region which receives at least a portion of the fluid output of the power turbine. A reformer is positioned downstream and is coupled to the duct region and the reformer has a fuel outlet which is coupled to the combustor.

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.

Abstract: Component members of a gas turbine engine are cooled by using an engine having a compressor for introducing air into the engine. A combustor is downstream from the compressor which has a casing, and a liner positioned in the casing. The liner is spaced apart from the casing such that a mixing region is positioned between the liner and the casing. The liner has a combustor inlet at the upstream end of the combustor. A turbine, which typically consist of one or more stages having cooling passages therein, is positioned downstream from the combustor. A steam conduit is connected to a steam inlet and the steam inlet is connected to the casing. The inlet has at least one inlet hole which connects the steam inlet with the mixing region and the inlet hole is downstream from the combustor inlet. A passageway is positioned between the mixing region and the turbine cooling passage and the passageway is downstream of the steam inlet hole.

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.

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.

Abstract: A steam piston balance means for a turbine engine comprises, in one form, a pressure chamber and means for supplying steam to the chamber to apply a force to walls of the chamber. The chamber is defined, in part, by an inner surface portion of a member connected and rotating with a portion of a thrust bearing whereby pressure force applied on the inner surface in turn applies a tractor force on the thrust bearing.