scispace - formally typeset
Search or ask a question

Showing papers on "Turbine published in 1993"


01 Feb 1993
TL;DR: The Natural Excitation Technique (NExT) is a method of modal testing that allows structures to be tested in their ambient environments as mentioned in this paper, and has been used extensively in the literature.
Abstract: The Natural Excitation Technique (NExT) is a method of modal testing that allows structures to be tested in their ambient environments This report is a compilation of developments and results since 1990, and contains a new theoretical derivation of NExT, as well as a verification using analytically generated data In addition, we compare results from NExT with conventional modal testing for a parked, vertical-axis wind turbine, and, for a rotating turbine, NExT is used to calculate the model parameters as functions of the rotation speed, since substantial damping is derived from the aeroelastic interactions during operation Finally, we compare experimental results calculated using NExT with analytical predictions of damping using aeroelastic theory

659 citations


Journal ArticleDOI
TL;DR: In this paper, variable rotor speed control of a fixed-pitch wind turbine is investigated on a system consisting of a wind turbine which can operate in a wide speed range, from 0 to 38 RPM.
Abstract: Variable rotor speed control of a fixed-pitch wind turbine is investigated on a system consisting of a wind turbine which can operate in a wide speed range, from 0 to 38 RPM. It produces any desired output from the rated (20 kW) to no-load, providing there is enough wind. A special technique is used to determine the operating point of the wind turbine by using the measured rotor speed and power. A difficult problem with this type of wind turbine control is to make the upper speed limit reasonably high to capture as much energy as possible but still low enough to avoid power peaks. >

213 citations


Journal ArticleDOI
TL;DR: The results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high pressure turbine vanes were reported in this article.
Abstract: This paper reports the results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high pressure turbine vanes. The specific materials tested were Mt. St. Helens ash and a soil blend containing volcanic ash (black scoria) from Twin Mountain, New Mexico. Hot section test systems were built using actual engine combustors, fuel nozzles, ignitors, and high pressure turbine vanes from an Allison T56 engine can-type combustor and a more modern Pratt and Whitney F-100 engine annular-type combustor. A rather large turbine inlet temperature range can be achieved using these two combustors. The deposition behavior of volcanic materials as well as some of the parameters that govern whether or not these volcanic ash materials melt and subsequently deposit are discussed.Copyright © 1992 by ASME

190 citations


Patent
22 Mar 1993
TL;DR: In this paper, a gas turbine engine cooling system is proposed to realize improved cooling of high-temperature constituent portions and other portions by using a turbocompressor and a heat exchanger.
Abstract: PURPOSE: To provide a gas turbine engine cooling system realizing improved cooling of high-temperature constituent portions and other portions. CONSTITUTION: A turbocompressor 128 and a heat exchanger 130 are fluidly interconnected and are each in fluid communication to receive air of differing pressures and temperatures. Typically, such air is received from various regions of an engine low pressure compressor and an engine high pressure compressor. A cooling system 110' delivers air through a duct 126 to a portion of the engine for cooling, such as the engine high pressure turbine region, at lower temperatures and higher pressures than if cooling air were directly ducted from the engine compressor to the engine turbine.

131 citations


Patent
29 Jan 1993
TL;DR: In this article, a catalytic bearing component of a gas turbine engine is provided, where the catalytic materials are selected from the group consisting of noble metals and transition metal oxides.
Abstract: A catalyst-bearing component of a gas turbine engine is provided. Catalytic materials are provided on components defining the gas flow path of the engine, so that emissions of carbon monoxide and unburned hydrocarbons are reduced. The catalytic materials are selected from the group consisting of noble metals and transition metal oxides. The portions of the gas flow path where such materials are advantageously applied include the combustor, the turbine and the exhaust system. The catalytic coating is preferably applied in conjunction with a thermal barrier coating system interposed between a substrate component and the catalytic coating.

103 citations


Patent
17 Dec 1993
TL;DR: In this article, an air flow controllable register unit for controlling flow of air through the register from an air circulating system having a register air flow supply duct is presented, where the air flow is controlled in response to an externally provided control signal that commands the register flow control unit to provide differing air flow rates.
Abstract: The invention relates to an air flow controllable register unit for controlling flow of air through the register from an air circulating system having a register air flow supply duct. The air flow is controlled in response to an externally provided control signal that commands the register flow control unit to provide differing air flow rates through the register. The register unit includes a register flow control apparatus which has a power generating device that includes a rotary mounted air turbine positioned within the register air flow supply duct. The air turbine is coupled to a generator to drive the same upon air flow against blades of the turbine. The air driven turbine initially restricts air flow of the register at system start-up. A blade pitch control device is coupled to the blades and is responsive to the air turbine rotary speed to cause the blades to rotate into an air flow restricting position when the air circulating system is at start-up with system air flow rates at a minimum and into a reduced air flow restriction position allowing higher air flow rates when the rotary turbine speed has increased. The register flow control apparatus is responsive to the externally provided control signal to provide a loading of the generator so that the air turbine is braked to thereby reduce the rotary turbine speed and cause the blade pitch control device to rotate the blades into an air flow restricting position which produces a lower air flow rate from the register.

94 citations


Patent
19 Feb 1993
TL;DR: In this article, a swimming pool cleaning device has a hollow housing supported on two pairs of device mover wheels (14,16) and pivoted directional control floats, which swing shift within the housing to shift the shift gears in response to the impact of the cleaning device on an obstruction on the pool floor or by the device impacting a vertical pool wall.
Abstract: A vacuum powered automatic swimming pool cleaning device (10) has a hollow housing supported on two pairs of device mover wheels (14,16). The housing includes a central water suction chamber in water flow communication with a water suction trough (34) at the bottom of the housing and in water outlet communication with an external vacuum line, a gear train for driving one of the pairs of mover wheels (14,16), and pivoted directional control floats. The water suction chamber houses an axle mounted turbine wheel bearing water driven vanes with the turbine being rotated in one direction only by water flow through the chamber. The turbine axle bears a turbine power output drive gear which intermeshes with one or the other of two shift gears which in turn reversibly drive the gear train as dictated by the position of the directional control floats within the housing. The floats swing shift within the housing to shift the shift gears in response to the impact of the cleaning device on an obstruction on the pool floor (pf) or by the device impacting a vertical pool wall. The swing shift of the control floats reverses the rotation of the mover wheels (14,16) and thus the direction of movement of the cleaning device (10) on the pool floor (pf).

93 citations


Patent
06 Aug 1993
TL;DR: In this paper, a method for supplying cooling air on vehicles such as high speed aircraft includes diverting high pressure air from the compressor section of a gas turbine engine, cooling this air in a heat exchanger, and expanding the diverted high-pressure air through an auxiliary turbine.
Abstract: A method for supplying cooling air on vehicles such as high speed aircraft includes diverting high pressure air from the compressor section of a gas turbine engine, cooling this air in a heat exchanger, and expanding the diverted high pressure air through an auxiliary turbine. Coolant in the heat exchanger may be inlet ram air, fan air, or aircraft fuel (which may be endothermic), and the coolant is ultimately introduced into the engine downstream of the compressor section. An auxiliary compressor may be used to further compress the diverted high pressure air or coolant prior to the flowing thereof through the heat exchanger, and one or more auxiliary turbines may be used to power the auxiliary compressor, or mechanical accessories on the vehicle.

93 citations


Patent
16 Apr 1993
TL;DR: The solar venturi turbine as mentioned in this paper is an upwardly oriented venturi tube supported by a venturi support skirt, which allows sunlight to project therethrough and impinge on a tapered centrifugal fan fronting the thermopane enclosure.
Abstract: A solar venturi turbine includes an upwardly oriented venturi tube supported by a venturi support skirt. The venturi tube includes a tapered thermopane glass enclosure which allows sunlight to project therethrough and impinge on a tapered centrifugal fan fronting the thermopane enclosure and mounted within the venturi tube. Located above the centrifugal fan in the neck of the venturi tube is a high velocity fan. A high pressure compressor is mounted above the high velocity fan, and finally a turbine is mounted above the high pressure compressor. A venturi tube outlet flares outwardly directly above the turbine and is mounted to the venturi tube. The turbine is connected to a shaft to drive an electrical generator thereby producing electricity. The sun's rays heat the air within the thermopane glass enclosure causing the reduced density air to rise within the venturi tube and propel the centrifugal fan. The air continues upwardly through the high speed fan and the high pressure compressor increasing in velocity and finally passing through and turning the turbine which is connected to the generator by the turbine shaft. Initial start-up of the solar venturi turbine is with a motor which turns both fans and the high pressure compressor. The solar venturi turbine provides a clean and environmentally harm-free source of electricity without diminishing fossil fuel reserves.

89 citations


Patent
03 Feb 1993
TL;DR: In this paper, a gear train is selectively operatively joined between the first and second shafts by selectively engaging a first clutch for transmitting torque through the first clutch only in one direction from the first shaft to the second shaft.
Abstract: A method and assembly are effective for air-starting an aircraft gas turbine engine having a fan powered by a low pressure turbine through a first shaft, and a compressor powered by a high pressure turbine through a second shaft disposed coaxially therewith. A gear train is selectively operatively joined between the first and second shafts by selectively engaging a first clutch for transmitting torque through the first clutch only in one direction from the first shaft to the second shaft when the fan is windmilling for driving the second shaft to allow an air-start of the gas turbine engine during flight. In a preferred embodiment, a second clutch is operatively joined to the gear train and is selectively engageable at speeds of the second shaft below a predetermined release speed, and disengageable at the release speed and above for disconnecting the air-start assembly once the engine has been started.

89 citations


Patent
28 Apr 1993
TL;DR: An airfoil for a gas turbine engine is constructed from a core body formed of conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy as discussed by the authors.
Abstract: An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy. The nickel aluminide components exhibit a high degree of thermal conductivity and efficiently transfer heat into the core body by direct conduction.

Patent
18 Nov 1993
TL;DR: In this article, a fuel trimming unit was adapted to each combustion chamber in a multi-chamber combustor of an industrial gas turbine to adjust the fuel-air mixture to account for air flow variations into the individual combustion reaction zones of each chamber.
Abstract: A fuel trimming unit has been adapted to each combustion chamber in a multi-chamber combustor of an industrial gas turbine. The fuel trim unit matches the combustion air flow into each combustion chamber. This adjusts the fuel-air mixture to account for air flow variations into the individual combustion reaction zones of each combustion chamber. Because of the fuel trim unit, a uniform fuel-air mixture is provided to each combustion chamber in a gas turbine. The fuel trim unit is adjusted using sensor inputs of the fuel flow rate to each combustion chamber, the dynamic pressure in each combustion chamber, and the turbine exhaust temperature.

Patent
06 Oct 1993
TL;DR: In this article, a dental handpiece having a cleaning unit contains a turbine gas supply passage for supplying a gas under pressure to a turbine for rotationally driving a dental tool, a rinsing liquid supply passage and a chip-scattering gas supplying passage for scattering cut chips produced by operation of the dental tool.
Abstract: A dental handpiece having a cleaning unit contains a turbine gas supply passage for supplying a gas under pressure to a turbine for rotationally driving a dental tool, a rinsing liquid supply passage for supplying a rinsing liquid to a turbine head, a chip-scattering gas supply passage for supplying a gas for scattering cut chips produced by operation of the dental tool, and a cleaning unit for cleaning at least one of the gas and the liquid provided in at least one of the turbine gas supply passage the rinsing liquid supply passage and the chip-scattering gas supply passage.

Patent
15 Oct 1993
TL;DR: In this paper, a method and apparatus for increasing blade fatigue strength in a turbine engine is presented, where the blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engines, thus increasing the blade fatigue.
Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

Patent
27 May 1993
TL;DR: In this paper, an integrated turbine and generator includes a power turbine having counter-rotating outer and inner rotor blades extending from respective inner and inner rotors, supported by stationary front and rear frames.
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. In a preferred embodiment, a tractor piston is joined to the inner rotor and a pusher piston is joined to the outer rotor and both provided with steam under pressure for generating forward thrust forces thereagainst for balancing aft thrust forces from the outer and inner blades carried through front and rear thrust bearings to the front and rear frames.

Patent
30 Aug 1993
TL;DR: In this paper, a rotor hub is provided for coupling a wind turbine rotor blade and a shaft, and two teeter control mechanisms, which may include hydraulic pistons and springs, are connected to the rotor blades and to the yoke at extension portions.
Abstract: A rotor hub is provided for coupling a wind turbine rotor blade and a shaft. The hub has a yoke with a body which is connected to the shaft, and extension portions which are connected to teeter bearing blocks, each of which has an aperture. The blocks are connected to a saddle which envelops the rotor blade by one or two shafts which pass through the apertures in the bearing blocks. The saddle and blade are separated by a rubber interface which provides for distribution of stress over a larger portion of the blade. Two teeter control mechanisms, which may include hydraulic pistons and springs, are connected to the rotor blade and to the yoke at extension portions. These control mechanisms provide end-of-stroke damping, braking, and stiffness based on the teeter angle and speed of the blade.

Patent
12 May 1993
TL;DR: In this article, a method and system for increasing the pressure of gaseous fuel delivered to a fuel system of a gas turbine engine is described, where a portion of pressurized gas or compressed air is discharged from a high-pressure section of the gas turbine and is communicated to a plurality of radial inflow turbines or axial flow turbines.
Abstract: A method and system for increasing the pressure of gaseous fuel delivered to a fuel system of a gas turbine engine. A portion of pressurized gas or compressed air is discharged from a high-pressure section of the gas turbine engine and is communicated to a plurality of radial inflow turbines or axial flow turbines. Energy is transferred from each turbine to a plurality of compressors driven by the turbines. Gaseous fuel is supplied to an inlet of one of the compressors. The compressed gaseous fuel is then cooled downstream of the compressors. The aftercooled and compressed gaseous fuel is delivered to the fuel system of the gas turbine engine.

Patent
23 Aug 1993
TL;DR: In this article, an air cycle machine for producing a supply of cooled air and including a compressor rotor fixed to a shaft which is driven by a turbine rotor, the turbine serving to expand air which is pressurized by the compressor.
Abstract: An air cycle machine for producing a supply of cooled air and including a compressor rotor fixed to a shaft which is driven by a turbine rotor, the turbine serving to expand air which is pressurized by the compressor. Magnetic bearings support the shaft radially in a housing for rotation about a precisely established axis while a magnetic thrust bearing keeps the shaft in a precisely fixed axial position. The housing and the bearings are constructed as two split sections to permit the housing and the bearings to be separated radially and facilitate repair and/or replacement of the shaft and other internal components.

Patent
23 Sep 1993
TL;DR: In this article, a gas turbine engine with a turbine vane assembly including an integrally cast cooling fluid nozzle is described, where the leading edge is tapered such that in a most open position of the turbine Vane assembly, the angled leading edge aligns with the trailing edge such that a step down is created in the circumferentially directed flow of the sealed cavity.
Abstract: A gas turbine engine having a turbine vane assembly including an integrally cast cooling fluid nozzle (86) is disclosed. Various construction details are developed which disclose a cooling fluid nozzle including a flow passage (108) having an exit (112) and a wall means (114). In one embodiment, the wall means includes an angled leading edge (118) which mates with a circumferentially adjacent trailing edge (122) of an adjacent wall means. The leading edge is tapered such that in a most open position of the turbine vane assembly the leading edge and the trailing edge circumferentially align. In a most closed position of the turbine vane assembly, the angled leading edge aligns with the trailing edge such that a step down is created in the circumferentially directed flow of the sealed cavity. The plurality of wall means thereby produce a waterfall arrangement within the sealed cavity to reduce the windage losses.

Journal ArticleDOI
TL;DR: A team approach involving several turbine engine companies using the concepts of simultaneous engi-neering has been used to successfully develop CMSX-4 ® alloy for turbine blade applications.
Abstract: A team approach involving several turbine engine companies using the concepts of simultaneous engi-neering has been used to successfully develop CMSX-4 ® alloy for turbine blade applications. CMSX-4 al-loy is a second-generation, single-crystal cast nickel-base superalloy containing 3% Re and approximately 70% volume fraction of γ. The high level of balanced properties determined by labora-tory evaluation has been confirmed during field testing of the Solarγ Mars T-14000 industrial gas turbine with CMSX-4 single-crystal (SX) blades in both the coated and bare condition. A similar collaborative ap-proach has resulted in the successful development of CM 186 LCγ alloy for complex, directionally solidi-fied (DS) columnar grain vane segments. CM 186 LC alloy is a second-generation DS columnar grain cast nickel-base superalloy containing 3% Re and approximately 65% volume fraction of γ. Excellent com-ponent producibility and quality is demonstrated. Turbine engine testing is scheduled to commence by the end of 1993.

Patent
08 Apr 1993
TL;DR: In this paper, a gas turbine engine having improved output horsepower and a method of achieving it is described, where the engine has, in order, a low pressure compressor, a high pressure compressor and a combustor, with a speed reducing gear box there between.
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.

Journal ArticleDOI
01 Sep 1993-Energy
TL;DR: In this paper, a multi-component (NB 3 /H 2 O) Kalina-type cycle that utilizes the exhaust from a gas turbine was investigated, where the turbine-inlet pressure of 5.96 × 10 6 N/m 2 and temperature of 755.372 K were kept constant, as well as the working fluid temperature at the condenser outlet.

Patent
18 Jun 1993
TL;DR: In this paper, an integrated aircraft power unit providing the electrical and other forms of energy needed during auxiliary power unit operating conditions-while the aircraft is on the ground, and also providing airborne or emergency power including high altitude flight emergency conditions power wherein the power unit uses an oxidant supply carried by the aircraft.
Abstract: An integrated aircraft power unit providing the electrical and other forms of energy needed during auxiliary power unit operating conditions-while the aircraft is on the ground, and also providing airborne or emergency power including high altitude flight emergency conditions power wherein the power unit uses an oxidant supply carried by the aircraft. In this high altitude operating condition the power unit provides lower electrical output, but lower losses and improved efficiency over previous power units. The disclosed power unit includes separate electromechanical transducers or motor generator devices coupled to a segregated pair of rotational shaft members, one for the inlet or compressor fan and one for the outlet or exhaust turbine fan with electrical coupling and then friction clutch coupling of these shafts accomplished for low altitude high energy output operation of the power unit. The described power unit is also capable of providing these aircraft energy needs with a minimum of physical changes from conventional integrated aircraft power units.

Patent
30 Sep 1993
TL;DR: In this paper, a water sprinkler unit for distributing water from a source over an area of terrain comprises a tubular housing having an inlet connected by a passage to an outlet, a distributor head mounted at the outlet for rotation about an axis for distribution of water via a nozzle, a turbine wheel disposed in the housing passage and operatively connected for driving the distributor head, and a turbine stator assembly having a passage including a throttling device for controllably directing a first portion of water to the turbine wheel.
Abstract: A sprinkler unit for distributing water from a source over an area of terrain comprises a tubular housing having an inlet connected by a passage to an outlet, a distributor head mounted at the outlet for rotation about an axis for distribution of water via a nozzle, a turbine wheel disposed in the housing passage and operatively connected for driving the distributor head, and a turbine stator assembly having a passage including a throttling device for controllably directing a first portion of water to the turbine wheel, and a pressure responsive valve for controllably diverting a second portion of the water around the turbine wheel in proportion to the pressure thereof for maintaining the speed of the turbine substantially constant.

Journal ArticleDOI
TL;DR: In this paper, experimental documentation and analytical correlations demonstrating the effects of hot streak accumulation and phantom cooling on turbine rotor airfoil surface temperature were presented, and experimental results were shown for a range of controlling variables to identify where streak accumulation was most likely to be strongest.
Abstract: This paper presents experimental documentation and analytical correlations demonstrating the effects of hot streak accumulation and phantom cooling on turbine rotor airfoil surface temperature. Results are shown that quantify the impact of (1) a nonuniform temperature profile at the entrance of a turbine due to combustor-generated hot and cold streaks, and (2) cooling air discharged from the trailing edge of the upstream stator. In Part 1 of this paper, experimental results are shown for a range of controlling variables to identify where streak accumulation and phantom cooling were most likely to be strongest

Journal ArticleDOI
TL;DR: In this article, hot-film probe measurements were made downstream of every rotor blade row of a five-stage low-pressure turbine and rotor-rotor interaction and stator rotor interaction were observed to have a profound influence on the flow through the low pressure turbine.
Abstract: The objective of this work was to enhance the understanding of unsteady flow phenomena in multistage low-pressure turbines. For this purpose, hot-film probe measurements were made downstream of every rotor blade row of a five-stage low-pressure turbine. Rotor-rotorr interaction and stator-rotor interaction were observed to have a profound influence on the flow through the low-pressure turbine. Interaction of rotors of different turbine stages occurred owing to the influence of the wakes shed by one rotor blade row upon the flow through the next downstream rotor blade row. This wake-induced rotor-rotor interaction resulted in strongly amplitude-modulated periodic and turbulent velocity fluctuations downstream of every rotor blade row with the exception of the most upstream one

Patent
09 Aug 1993
TL;DR: In this article, a U-shaped wear shim assembly for protecting selected wear surfaces on the engine casing of a gas turbine engine has been presented, namely a radial seating surface and an axial seating surface.
Abstract: A wear shim assembly is provided which includes a substantially U-shaped wear shim for protecting selected wear surfaces on the engine casing of a gas turbine engine. The wear shim advantageously simultaneously protects multiple surfaces of the engine casing, namely, a radial seating surface and an axial seating surface of the engine casing, from undesired differential thermal expansion wear and vibrational wear.

Patent
02 Aug 1993
TL;DR: A gas turbine engine ducted to have the air pass sequentially through a single stage axial flow compressor, a single-stage hybrid axial-radial centrifugal compressor and a burner, an inward flow radial turbine, an axialflow, high-pressure turbine, and then exit nozzles.
Abstract: A gas turbine engine ducted to have the air pass sequentially through a single stage axial-flow compressor, a single-stage hybrid axial-radial centrifugal compressor, a burner, an inward flow radial turbine, an axial-flow, high-pressure turbine, and then exit nozzles. The axial compressor and axial turbine are on a common core shaft. The centrifugal compressor and the radial turbine are on a common porous hub and form an integral, modular unit in which forces on the radial turbine blades drive the centrifugal compressor. The porous common hub permits air to transpire from the compressor to the turbine, serving to cool the turbine. Fuel is burned in annular, "folded-comma" shaped burners with multiple fuel-injection and ignition zones (two stage combustion). The gas flow path has an outer annular duct, a first inner duct from the burner, and a second inner duct to the burner. The outer duct shares common walls with the first and second inner ducts. The first inner duct is located between the burner and the outer duct. The second inner duct is located between the outer duct and a portion of the turbine section.

Patent
30 Aug 1993
TL;DR: In this article, a hydrogen-fuelled gas turbine with an inlet, an outlet and a rotatable member disposed in a flow path between the inlet and the outlet is presented.
Abstract: A hydrogen fuelled gas turbine which includes a combustion chamber having a steam inlet, an oxygen inlet, a hydrogen inlet, and an outlet. A compressor is provided. The steam inlet is connected to the compressor such that the compressor provides steam as a working fluid. The hydrogen inlet is connected to a source of hydrogen gas, whereby hydrogen gas serves as a fuel for combustion. The oxygen inlet is connected to a source of oxygen gas, whereby oxygen is supplied to oxidize the hydrogen fuel. An igniter is disposed within the combustion chamber whereby the hydrogen/oxygen mixture is explosively ignited. The products of combustion combine with the steam and rapidly expand out through the outlet of the combustion chamber. A turbine is provided having an inlet, an outlet and a rotatable member disposed in a flow path between the inlet and the outlet. The inlet of the turbine is connected to the outlet of the combustion cheer such that expanding products of combustion and steam exert a force to rotate the rotatable member when passing from the inlet to the outlet. The compressor has an inlet coupled with the outlet of the turbine whereby steam from the outlet of the turbine is recycled. The compressor has a plurality of water injectors adapted for connection to a water source whereby water is injected into the steam such that the water draws heat from the steam as it vaporizes thereby triggering a physical volume reduction.

Journal Article
TL;DR: In this paper, an impulse turbine with self-pitch-controlled guide vanes was investigated experimentally by the use of turbine test equipment in which the sinusoidally reciprocating flow conditions are simulated.
Abstract: An impulse turbine with self-pitch-controlled guide vanes was proposed by the authors in a previous paper. The unsteady characteristics of this turbine have been investigated experimentally by the use of turbine test equipment in which the sinusoidally reciprocating flow conditions are simulated. The results have been compared with those of a Wells turbine. Furthermore, in order to clarify the usefulness of quasi-steady analysis of this turbine, they have been also compared with the analytical results calculated on the basis of the experimental data obtained by the model testing of a turbine rotor with fixed guide vanes under steady unidirectional flow conditions. As a result, it has been clarified that the impulse turbine presented here is superior to the Wells turbine in overall characteristics, and the quasi-steady analysis is available for this turbine.