Showing papers on "Ram air turbine published in 2004"

Method and system for control of turbogenerator power and temperature

Abstract: A power controller controls the turbine of a turbine powered generating system regardless of the load on the system to maximize the efficiency of the turbine and maintains the turbine at a substantially constant temperature during a system load change by using an energy storage device to provide power to the load while the turbine is changing speed to meet the new load demand.

Gas turbine engine bleed air power assist system and method

Abstract: A bleed air power assist system is coupled to a gas turbine engine (100) that includes a high pressure turbine (126), a low pressure turbine (128), and an electrical generator (138) driven by the high pressure turbine (126). The bleed air power assist system selectively bleeds air discharged from the high pressure turbine (126) and supplies it to an air turbine (156) that is also coupled to the generator (138). Thus, the system selectively reduces the power extracted from the high pressure turbine (126). This, coupled with the bleed air that is diverted from the low pressure turbine (128), allows the low pressure spool (136) to run at lower speeds when high engine thrust is not needed or desired, but when the generator (138) is still needed to supply high electrical loads.

Laminar air turbine

Abstract: The windmill assembly is a low drag, streamlined body of revolution that captures the kinetic energy content of the accelerated laminar air surrounding the body. The assembly includes a power-generating, wind-driven turbine that is compact, lightweight and capable of producing a substantially greater output than a conventional windmill with a comparable size rotor. The turbine includes a protruding aerodynamic nose and outer cowling that provide a streamlined, wind-collecting inlet section that constricts the incoming air stream and increases its velocity through the turbine blades. The turbine further includes an exit section designed to exhaust the air stream with a minimum of turbulence. One or more generators are coupled to a turbine wheel, and are electrically switched on and off to maximize the energy capture over the full range of ambient winds. The wind turbine assembly may be configured around a blimp-type body having counter-rotating turbine assemblies.

Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines

Abstract: A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is provided. The secondary flow turbine cooling system provides uniform cooling air having a similar pressure and temperature in a recuperated gas turbine engine as the compressor discharge air of a non-recuperated gas turbine engine. A method for uniform cooling of high pressure turbine module components using the secondary flow turbine cooling air system is also provided.

Air turbine powered accessory

Abstract: An aircraft accessory system includes an aircraft engine powered direct air turbine driven accessory and an air turbine drivingly directly connected by an air turbine shaft to the accessory. The air turbine includes a variable geometry turbine nozzle in selectable direct flow communication with at least two compressed engine air sources. The two compressed engine air sources may be an HPC interstage bleed and an HPC compressor discharge stage bleed. The variable geometry turbine nozzle may be in selectable direct flow communication with a third compressed engine air source such as a bypass duct or an engine inlet duct. The air turbine includes a turbine exit which may be in selectable direct flow communication with at least two relatively lower pressure engine air sinks. The air sinks may be located in the aft end of a bypass duct and in a divergent section of the exhaust nozzle.

Microfabricated rankine cycle steam turbine for power generation and methods of making the same

Abstract: In accordance with the present invention, an integrated micro steam turbine power plant on-a-chip has been provided. The integrated micro steam turbine power plant on-a-chip of the present invention comprises a miniature electric power generation system fabricated using silicon microfabrication technology and lithographic patterning. The present invention converts heat to electricity by implementing a thermodynamic power cycle on a chip. The steam turbine power plant on-a-chip generally comprises a turbine, a pump, an electric generator, an evaporator, and a condenser. The turbine is formed by a rotatable, disk-shaped rotor having a plurality of rotor blades disposed thereon and a plurality of stator blades. The plurality of stator blades are interdigitated with the plurality of rotor blades to form the turbine. The generator is driven by the turbine and converts mechanical energy into electrical energy.

Turbo test rig with hydroinertia air bearings for a palmtop gas turbine

Abstract: This paper describes a turbo test rig to test the compressor of a palmtop gas turbine generator at low temperature (<100 °C). Impellers are 10 mm in diameter and have three-dimensional blades machined using a five-axis NC milling machine. Hydroinertia bearings are employed in both radial and axial directions. The performance of the compressor was measured at 50% (435 000 rpm) and 60% (530 000 rpm) of the rated rotational speed (870 000 rpm) by driving a turbine using compressed air at room temperature. The measured pressure ratio is lower than the predicted value. This could be mainly because impeller tip clearance was larger than the designed value. The measured adiabatic efficiency is unrealistically high due to heat dissipation from compressed air. During acceleration toward the rated rotational speed, a shaft crashed to the bearing at 566 000 rpm due to whirl. At that time, the whirl ratio was 8.

Single shaft combined cycle power plant and its operation method

Abstract: According to the invention, there is provided a single shaft combined cycle power plant which can quickly switch from single operation of a gas turbine to combined operation of the gas turbine and a steam turbine, and can quickly increase output power, from low power to high power. The single shaft combined cycle power plant includes a means for maintaining the rotation speed of the steam turbine at a speed slower than but near a rated rotation speed when the steam turbine is separated from a coupled unit of a generator and the gas turbine.

Development of an Advanced Microturbine System Using Humid Air Turbine Cycle

Abstract: A prototype machine for a next generation microturbine system applying a simple humid air turbine system (design target of electrical output: 150 kW, electrical efficiency: 35% LHV) was developed for its laboratory evaluation. A low NOx combustor which applied a lean-lean zone combustion concept and water lubricated bearings were developed for the prototype machine. Operation using two water lines for the humid air turbine (HAT) was proposed as an effective way to obtain rated electric output to ambient temperature of 40 deg C. Tests for the main components were done successfully. Motoring tests, full speed test with no load, 50% load and 70% load tests as preliminary tests for rated load tests were also carried out successfully. Low NOx emission of 7.6 ppm and high efficiency of 95.6% for the power conversion system were achieved in the partial load tests. At the first rated load test without HAT and Water atomizing inlet air cooling (WAC) that followed those partial load tests, 150.3 kW electric output with electrical efficiency of 32% was obtained.© 2004 ASME

Gas turbine, in particular aircraft engine and method for generating electrical energy in a gas turbine

Abstract: The invention relates to a gas turbine, in particular an aircraft engine and to a method for generating electrical energy in a gas turbine. The gas turbine comprises at least one engine core (18), in which a shaft (19) produces a shaft output. The inventive turbine is equipped with means that generate electrical energy both from the shaft output produced by the engine core (18) and from the compressed air that is dissipated by the engine core (18).

Air turbine starter with angular contact thrust bearing

Abstract: An air turbine starter for use in aircraft or other gas turbine engine applications. In a particular embodiment, the air turbine starter has a thrust bearing (130) having an outer ring (302), an inner ring (304), a cage (308) and balls (306). The outer ring has a first shoulder (312), a second shoulder (314) and a race surface (316) therebetween to receive the bans. The second shoulder is smaller than the first shoulder. The orientation of the cage is such that the pilot of the cage is aligned to the first shoulder of the outer ring. The raceway curvature of the inner ring, the internal clearance (328), and clearance between the pilot (324) and outer ring are ail increased. An improved thrust bearing is also provided.

Turbine generator system and method

Abstract: In one embodiment, a wellbore power generation method includes causing a fluid to flow through a downhole turbine, and causing the turbine to rotate a generator (100). At least one of a turbine configuration and a flow rate of the fluid is selected to cause the downhole turbine to operate near its runaway speed, such that changes in load applied to the generator (100) do not substantially affect a rotation rate of the downhole turbine (111).

Arrangement and method for the generation of water on board an aircraft

Abstract: An arrangement and a method are proposed for the generation of water on board an aircraft with the use of one or more fuel cells, whereby low-temperature fuel cells are provided as fuel cells. It is proposed that several single-cell or few-cell fuel cells may form a fuel-cell panel or cell array and several cell panels or cell arrays may be arranged close to the inside of the aircraft fuselage and the cathode side of the at least one fuel cell has a chamber pointing to the exterior of the aircraft for the condensation of the water contained in the air and the anode side has a chamber carrying a combustion gas, for example hydrogen. With the proposed solution, a reduction in the storage capacity for drinking water and its quality-assured provision may be enabled and moreover, with the use of fuel cells as a virtual power station, the energy demand on engine generators, auxiliary power unit (APU) or ram air turbine (RAT) may be reduced.

Pressurized near-isothermal fuel cell - gas turbine hybrid system

Abstract: A hybrid fuel cell-gas turbine system and method efficiently generates power using a combination of separate power generating components. The system includes a turbine system having an air compressor and a turbine, and a fuel cell. By-product waste heat from the fuel cell is used within the fuel cell to heat the cathode air.

Ram air turbine over-speed protection using redundant yoke plate linear bearings

Abstract: An improved ram air turbine for generating emergency aeronautical supplemental power with a plurality of concentric or nested linear bearings for supporting a speed governor yoke plate on a speed governor shaft comprising a movable sleeve that supports the yoke plate and rides on the governor shaft.

Wind turbine generator and its power generation output control method

Abstract: PROBLEM TO BE SOLVED: To provide a wind turbine generator capable of efficiently converting wind energy to electric power even when the wind turbine generator is installed in a place in severe meteorological environment where air temperature and air pressure change sharply, and a power generation output control method for the wind turbine generator. SOLUTION: In this wind turbine generator, air density information (ρ) around the wind turbine generator is acquired by an air density information acquiring means 40. Optimum gain Kλ giving power generation output command for operating a wind turbine rotor at an optimum tip speed ratio λ is determined by an optimum gain setting part 31, on the basis of the air density information. Power generation output command Pdem instructing power generation amount based on the optimum gain Kλ and power generator rotational speed ω is output to a power generator system 15 by an output command setting part 32. COPYRIGHT: (C)2005,JPO&NCIPI

Electricity, heat and cool co-productive compressed air energy storage apparatus and method

Abstract: The invention discloses an electricity, heat and cool co-productive compressed air energy storage apparatus and method, wherein an air storage chamber and an air-water heat exchanger are connected intandem between the compressor and the heat regenerator, the heating tube in the air storage chamber is used for transmitting the heat energy carried by the air to the heat transfer medium, and supplying heat to the outside through the water channel of the air-water heat exchanger, an air is also connected between the compressor and the heat regenerator, the air flowing out from the air storage chamber flows through the air duct of the air-water heat exchanger and the hot air channel of the heat regenerator, which is cooled down and enters the air turbine for working by expansion, driving the electric generator for power generation, and transforming the air compression energy into electrical energy.

Ram air channel for the supply of ambient air in an aircraft

Abstract: A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to guarantee that the systems on board the aircraft are supplied, in a simple and reliable way, with the required ambient air in any operational state of the aircraft, ie. both during the flight and on the ground, the ram air channel (10) has a second air inlet (24) which is independent from the first air inlet (12).

A combination of an aircraft and a gas turbine engine

Abstract: The gas turbine engine comprises an intake, and a low pressure compressor having rotor blades 42 and stator vanes 45. To balance the circumferentially varying back pressure from a pylon 46, with a circumferentially varying forward flow pressure from the intake, the stagger angles of the stator vanes at different circumferential positions are arranged to differ.

Pressure/flow sensing stall recovery for a ram air turbine

Abstract: A stall recovery system for a ram air turbine (RAT) that supplements the operation of a volume fuse in the hydraulic system of the RAT by sensing a stall condition as the combination of low pressure at less than maximum flow and reducing RAT load torque after the sensed stall so that stall recovery is possible.

Generator wiring for producing controllable braking power operates during start-up/power reduction of a power engine driven by a generator

Abstract: A generator's stator (30S) and rotor (30L) interlink via an exciter circuit (50). Electric power is picked up by the stator so as to excite the rotor independently and the fed to the rotor via the exciter circuit, to which a further electric consumer (60) is wired so as to increase the braking power of the generator. Independent claims are also included for the following: (A) A turbine installation with a turbine like a steam/air turbine and a generator with a drive link to the turbine; (B) and for a method for producing controllable braking power during start-up/power reduction of a power engine with a drive link to a generator.

Internal combustion engine having air turbine device

Abstract: PROBLEM TO BE SOLVED: To provide an internal combustion engine having an exhaust turbocharger which maintains an air supply temperature of an engine at a low temperature, constantly keeps the air supply temperature at the temperature level of an outlet of an air cooler even when EGR gas is mixed in the air supply, improves the engine performance by increasing the weight and the flow rate of the air supply, and reduces a thermal load of the engine. SOLUTION: The internal combustion engine comprises an air turbine device having an expansion turbine provided in an air supply passage to drop a temperature by expanding air for combustion pressurized by an exhaust turbocharger and a compressor driven by the expansion turbine to pressurize outside air and a means to cool EGR gas by the air for combustion with the temperature dropped by the expansion turbine. COPYRIGHT: (C)2004,JPO

Process for filling a container with seeds comprises using an air turbine arranged in a sowing machine to produce a air stream, and conveying the seeds or similar material into the seed tank of the sowing machine

Abstract: Process for filling a container with seeds or similar material comprises using an air turbine arranged in a sowing machine or corresponding device to produce a air stream in connection with a Venturi tube, and conveying the seeds or similar material from a supply site or intermediate site into the seed tank of the sowing machine. The commercial operation of the turbine for conveying the seeds via distribution tubes can be switched to a turbine operation. Process for filling a container with seeds or similar material comprises using an air turbine (4) arranged in a sowing machine (1) or corresponding device to produce a air stream in connection with a Venturi tube (18), and conveying the seeds or similar material from a supply site or intermediate site into the seed tank (2) of the sowing machine. The commercial operation of the turbine for conveying the seeds via distribution tubes can be switched to a turbine operation. The overflow of the seed tank is stopped and the air stream is used to convey the seeds. An independent claim is also included for a feeding device for conveying seeds.

Ram air turbines

Abstract: A ram air turbine has blades 1 mounted on a hub 5. Inside the hub each blade 1 support a counterweight 60 arranged to alter the pitch of the blades as speed varies. Each counterweight 60 is coupled with an actuator 91 by which the angle of the blades can be altered remotely. The turbine is stopped rotating by altering the angles of the blades 1 such that the hub 5 rotates slightly in the reverse direction, which causes a sprag clutch 52 to lock the turbine 5. The actuator 91 is also coupled with an additional brake 100, which is applied after the clutch 52 locks.

Installation unit for generating wave energy of sea, has air turbine provided with floodgate that is provided at top part of main communication pit, and water turbine connected to electrical generator

Abstract: The unit has a cliff (1) whose barrier is positioned outside sea water A main communication pit (2) is formed with a pipe or conduit (6) The conduit is provided with an entrance gate (7) A water turbine (8) is connected to an electrical generator (11) A side of an upper secondary pit (3) is provided next to the main communication pit The upper secondary pit is formed with an air turbine (13) that is driven by the main communication pit during the filling process The air turbine is provided with a floodgate (12) that is provided at a top part of the main communication pit

Aircraft with integrated electrochemical supply system has electrochemical reactor as part of auxiliary drive for generating compressed air, electrical energy, ram air turbine, clear water tank, drive mechanism generator, oxygen supply

Abstract: The aircraft has a supply system with first electrochemical reactor (1) for generating energy, hydrogen, oxygen and clear water from grey water, hydrocarbon fuel and air, whereby the first reactor at least partly forms at least one of the systems selected from an auxiliary drive mechanism for generating compressed air and electrical energy, a ram air turbine, a clear water tank of a water system, a drive mechanism generator for generating electrical energy and an oxygen supply system.

Design considerations for an aerially towed vehicle with altitude holding capability

Abstract: *† Several unique design studies arise in the design of an aerial tow vehicle desired to have inherent stability and the ability to hold altitude from the surface using a single wing as a control surface. Cable interactions with aircraft performance and dynamics are studied using 2D static and dynamic simulations of the tow cable combined with classical aircraft performance and stability techniques. Trade studies include cable geometry selection, wing and tail sizing, cable attachment location, wing attachment location, center of gravity location, and the ramifications of vehicle weight. In addition, a ram air turbine (RAT) used to power onboard equipment is studied via wind tunnel to determine possible effects on vehicle performance and stability.

Hydraulic turbine or pump turbine

Abstract: Die Erfindung betrifft eine hydraulische Turbine oder eine hydraulische Pumpe - mit einem Laufrad, das eine Vielzahl von Schaufeln aufweist; - mit einer Laufradnabe. Gemas der Erfindung wird folgendes vorgesehen: - die Laufradnabe ist aus wenigstens zwei axial nebeneinander liegenden, zueinander koaxialen Teilen aufgebaut; - wenigstens ein Nabenteil ist in axialer Richtung verschiebbar.

A High Performance Optimized Reaction Blade for High Pressure Steam Turbines

Abstract: A higher efficiency gain is necessary for steam turbine plants to reduce their fuel consumption rate and lessen their environmental disruption factor. Power plant manufacturers have continued to make an effort to raise steam turbine internal efficiency by developing new technologies. High pressure (HP) steam turbines should have increased efficiency owing to relatively shorter blade height compared with other turbine sections (intermediate and low pressure turbines). In order to increase efficiency, it is important to improve the steam path determined by design parameters such as degree of reaction, number of stages and rotor diameter and to develop a high performance blade applied to it. The advanced computational fluid dynamics (CFD) technique is a useful design tool, and has come to be applied generally to evaluate energy loss. A new rotating blade has been developed for small and mid-class steam turbines with a shorter blade height. The robust design method, based on the statistical theory for design of experiments, is used for the blade root profile design. It is combined with the inverse method and 2-D turbulent blade-to-blade flow analysis to evaluate the aerodynamic performance. The blade configuration is expressed by four control factors, which are turning angle, leading edge radius, pitch-chord ratio and maximum blade loading location. Linear cascade experiments are also carried out due to verify the blade performance under the optimized conditions obtained by the robust design. Consequently, the blade section has a blunt-nose, flat incidence characteristics and low energy loss, compared with the conventional one and the optimized conditions given by the robust design are aerodynamically reasonable. Finally, air turbine model tests and 3-D Reynolds-averaged Navier-Stokes analyses are performed to investigate the detailed flow pattern and stage performance of the new optimized reaction blade. An experimental investigation is still important to evaluate the performance in the real turbine stage structure, while the numerical analysis method is used based on the implicit TVD scheme with the modified k-e turbulence model. It is found that the new optimized reaction blade has greatly improved stage efficiency of about 1.5% at the design point including the effect of leakage flow (3% improvement in stage efficiency excluding leakage flow) and realized an increase of pitch-chord ratio by about 35%. Consequently, the new optimized reaction blade is considered effective to raise the internal efficiency of the high-pressure steam turbine with improved steam path.Copyright © 2004 by ASME