Showing papers on "Turbine published in 1971"

The Computation of Transonic Flow Through Two-Dimensional Gas Turbine Cascades

Abstract: Steady transonic flow through two-dimensional gas turbine cascades is efficiently predicted using a time-dependent formulation of the equations of motion An integral representation of the equations has been used in which subsonic and supersonic regions of the flow field receive identical treatment Mild shock structures are permitted to develop naturally without prior knowledge of their exact strength or position Although the solutions yield a complete definition of the flow field, the primary aim is to produce airfoil surface pressure distributions for the design of aerodynamically efficient turbine blade contours In order to demonstrate the accuracy of this method, computed airfoil pressure distributions have been compared to experimental resultsCopyright © 1971 by ASME

Gas turbine power plants

Abstract: A gas turbine power plant comprising a compressor, a turbine and a system for transmitting the drive from the turbine to the compressor, wherein the transmission system comprises at least one homopolar electrical machine connected to the turbine and operating as generator, and at least one homopolar electrical machine connected to the compressor and operating as motor, wherein this motor is supplied with electrical current from the said generator.

Means for rapidly heating interior of a motor vehicle

Abstract: A HEATING SYSTEM FOR AN AUTOMOBILE PASSENGER COMPARTMENT WHICH INCLUDES A TURBINE TYPE COOLANT PUMP DRIVEN BY THE AUTOMOBILE ENGINE TO WARM ENGINE COOLANT AND PUMP IT THROUGH A HEATER IN THE PASSENGER COMPARTMENT. THE TURBINE PUMP HAS A HOUSING WHICH DEFINES AN ANNULAR FLUID PASSAGE BETWEEN THE PUMP INLET AND PUMP OUTLET. TURBINE BUCKETS FORMED ALONG THE PERIPHERAL EDGE OF A ROTATABLE IMPELLER WITHIN THE PUMP HOUSING MOVE THROUGH THE ANNULAR CHANNEL TO HEAT COOLANT THEREIN BY MEANS OF IMPACT OF THE TURBINE BUCKETS UPON THE COOLANT.

Turbine blade seal arrangement

Abstract: A seal arrangement for a turbine assembly including a turbine wheel, having a plurality of circumferentially arranged blades with adjacent edges of the blades being axially arranged above passages in the wheel assembly and retaining members arranged on each axial side of the wheel, a seal assembly between each adjacent pair of blades including an elongated seal member with means for maintaining the seal member in alignment with an axial recess formed by adjacent edges of the blade so that the seal member is urged radially outwardly into sealing engagement with the blades during rotation of the wheel and annular seal rings for maintaining sealing engagement between the retaining members and the plurality of blades.

Combined gas-steam turbine power plant

Abstract: In a combined gas-steam turbine power plant, part-load heat rate is improved by recirculating the boiler stack gas into the air inlet of the turbine compressor section.

Dual flow cooled turbine arrangement for gas turbine engines

Abstract: Turbine blading for a gas turbine engine includes a dual source of turbine cooling airflow wherein a portion of the high pressure compressor discharge airflow is directed to cool the most critical temperature areas of the turbine blade and a portion of the low pressure compressor interstage airflow is directed to cool the less critical temperature areas of the same turbine blade. The invention herein described was made in the course of or under a contract or subcontract thereunder (or grant) with the Department of the Navy.

Control of noise and instabilities in jet engines, compressors, turbines, heat exchangers and the like

Abstract: Intrinsic sound, noise and instabilities directly or indirectly due to the shedding of cross-stream vortices caused when air or fluid moves over the trailing edge of a plate, blade, vane or the like are reduced by the formation of relatively steady-state streamwise vortices upstream of the terminal edge. The invention is applied to turbine and compressor blades, jet tube inlets and exits, heat-exchanger tubes and the like by placing or forming streamwise vortex-inducing generators within the boundary layer on the shedding item so that the induced streamwise vortices trail off of the trailing edge and suppress the formation of cross-stream disturbances. Through this process, noise disturbances which would otherwise amplify to high sound intensitites and/or large flow disturbances, high structural stresses and loss of efficiency through passage over successive shedding items are suppressed in their early stages of development.

Turbo-compressor-pump

Abstract: A turbo-compressor-pump unit utilizing a common working fluid in the turbine, compressor, pump, and as libricant. A dynamic sealing and bearing means maintains separation of the working fluid at different energy or pressure levels within the turbocompressor-pump unit.

Gas turbine temperature profiling structure

Abstract: An axial flow gas turbine having a structure including a fuel nozzle for providing any desired turbine inlet temperature profile according to the mechanical stress on the rotating turbine blades. The fuel nozzle may be a combined multiple fuel gas and liquid type or a single fuel type, an important feature of both being the provision of fuel injection asymmetrically into the combustion chamber to establish a desired ignited fuel temperature pattern therein which continues down to the turbine inlet. This asymmetrical fuel supply into the combustion chamber is obtained by providing a number or size of fuel jets according to the temperature desired; for example, to provide a temperature gradient decreasing in an inward turbine radial direction through the combustor to correspond to the desired turbine blade inlet temperature profile. The angular jet direction also may be varied for different parts of the fuel injection pattern to obtain a further spatial control of the fuel injection distribution into the combustor. These fuel distribution control variables may be used singly or in any combination, and the same or different ones may be used for the gas and liquid jets in multiple fuel nozzles. In addition, a further modification of the intake temperature profile may be obtained by providing relatively cool jets of gaseous fluid through spaced orifices in the radially inner sides of the transition passages which direct the high temperature working gas to the turbine blades.

Method of continuously vaporizing and superheating liquefied cryogenic fluid

Abstract: The present invention relates to a method of continuously vaporizing and superheating liquefied cryogenic fluid for an ultimate use. A stream of liquefied cryogenic fluid is passed in heat exchange relationship with a stream of ambient water so that the cryogenic fluid is heated and vaporized. The vaporized cryogenic fluid stream is divided into first and second portions and the first portion is passed in heat exchange relationship, with the input combustion air to a gas turbine engine so that the air is cooled and the power output of the turbine increased. The second portion is passed in heat exchange relationship with the exhaust gases generated by the gas turbine engine so that the second portion is superheated to a predetermined temperature level, and the first and second portions of the vaporized cryogenic fluid stream are then combined so that a stream of vaporized cryogenic fluid superheated to a desired temperature level is produced. The power output of the gas turbine is advantageously used for providing power for pumping the streams of liquefied cryogenic fluid and ambient water.

Combination liquefied natural gas expansion and desalination apparatus and method

Abstract: A method and combined apparatus for vaporizing liquefied natural gas and expanding the gas through a turbine for generating power is described. The energy for heating the liquefied natural gas for vaporization is obtained by transferring heat from sea water or other saline water. The water, so cooled, is then passed to a vacuum freezing, vapor compression system for obtaining fresh water and brine. In another embodiment, cooling of sea water is obtained from cold natural gas already expanded through a first turbine for producing shaft horsepower. Energy for vaporizing and expanding the liquefied natural gas is obtained by transferring heat from compressed air. The air so cooled is liquefied and fractionated to produce liquid nitrogen and either liquid or gaseous oxygen. In both embodiments shaft horsepower from the turbines is coupled to the compressor of the vacuum freezing, vapor compression apparatus. The power available from natural gas expansion is augmented by power from a steam or gas turbine. Waste heat from the turbine is employed for distillation desalination. If desired, an electrical generator can be coupled to the turbines for providing peaking power.

Seal ring for gas turbine

Abstract: A gas turbine blade tip ring seal, which surrounds the blade tips to minimize turbine gas leakage around the blades, that incorporates a thermal protection system that allows modulation of the seal leading edge temperature level and thermal response to minimize seal deterioration during turbine transient operating conditions.

Effect of additives on mass transfer in turbine aeration

Abstract: Mass transfer coefficients and interfacial areas were determined for the aeration of aqueous solutions in a turbine agitated vessel. The mass transfer coefficients measured for water without additive and for sodium chloride solutions matched very well to measurements in the literature for air bubbles of the same diameter in free rise. Thus the only effect of agitation was to determine the bubble size which then in turn set the coefficient. Two surface active agents were studied: sodium dodecyl sulfate and Dow Corning Antifoam C. The rate of mass transfer increased with the former additive but decreased with the latter; however, the mass transfer coefficient was the exact same function of bubble diameter in both cases and the different rates are attributed to the quite different effects on interfacial area.

Composite gas turbine set

Abstract: A composite gas turbine set comprising a large main gas turbine set and a small auxiliary gas turbine set disposed in parallel arrangement for the production of regenerative cycles. A portion of the gas issued from a compressor of the main gas turbine set is applied to a compressor of the auxiliary gas turbine set. The exhaust gas which has provided regeneration in the auxiliary gas turbine set is applied to the turbine of the main gas turbine set. The composite turbine set is arranged so as to minimize increases in fuel consumption under widely variable load conditions.

Method and apparatus for controlling a power transmission

Abstract: In a transmission having a torque converter and a gear set wherein a ratio shift is accomplished by disengaging a brake or clutch and engaging another, a smooth shift is effected by controlling the clutch or brake pressures as a function of continuously computed values of turbine torque, turbine acceleration, and instantaneous gear ratio. These three parameters are computed by electronic analog circuitry from measured values of engine speed, turbine speed and transmission output speed. A logic circuit responsive to shift command, turbine speed and output speed conditions the analog circuit for operation. The analog output signal is converted to pressure by a solenoid valve.

Transmission having a converter clutch and a control

Abstract: A transmission and control having a limited slip clutch located between the impeller and turbine members of the torque converter to improve transmission efficiency and reduce heat losses. A valve member responsive to turbine speed is incorporated in the control for controlling the engagement force on the clutch thereby controlling the amount of slip between the torque converter impeller and turbine members. A control valve is also included to prevent engagement of the clutch except when the high gear ratio is established in the transmission.

Adjustable-blade turbine

Abstract: A gas turbine engine is shown in which the turbine nozzle vanes and turbine outlet guide vanes are simultaneously pivotal to obtain greater efficiencies over a broad range of gas stream energy levels.

Empirical expressions for estimating length and weight of axial-flow components of VTOL powerplants

Abstract: Simplified equations are presented for estimating the length and weight of major powerplant components of VTOL aircraft. The equations were developed from correlations of lift and cruise engine data. Components involved include fan, fan duct, compressor, combustor, turbine, structure, and accessories. Comparisons of actual and calculated total engine weights are included for several representative engines.

Heat vapor differential engine

Abstract: A heat engine consisting of a hermetically vapor vacuum sealed container and a heat-transfer fluid circuit, the fluid circuit including a heat source such as a solar heat collector. The engine employs as a working fluid a liquid with a low boiling point in the container, the heat transfer circuit passing through the lower portion of the container so that heat is conducted therefrom to the working fluid, causing bubbles to be generated therein. The bubbles flow upwardly and drive a turbine assembly mounted in the upper portion of the container. The turbine assembly is magnetically coupled to an external load device. The top of the container consists of a condenser exposed to ambient temperature wherein the bubbles are condensed and returned to a liquid state.

Rotary turbine engine

Abstract: Intake air undergoes two stage compression within a pair of coaxially mounted, counter-rotating rotors of a radial turbine engine and is tangentially discharged into a turbine mounted by one of the rotors. The air is heated and accelerated by discharge of combustion products from fuel burners mounted on the second stage compressor vanes in the other of the rotors to produce reaction thrust. Extensions of some of the second stage compressor vanes form discharge passages for the mixture of air and combustion products.

Optimisation of Turbo-Generator Transient Performance by Differential Dynamic Programming

Abstract: Methods which have been proposed for increasing the margin of stability in large generators generally act by controlling the generator electrical power output. A more direct control of the stability can be achieved by regulating the power input to the turbine. Simultaneous control of the field excitation and the turbine

Transpiration cooled turbine blade with metered coolant flow

Abstract: A turbine stator blade having a porous skin covering a strut member with channels for cooling air fed from the root, and a removable metering plate attached to the root and having orifices of various sizes for transmitting air to the blade channels, the metering plate being selected for having appropriate orifices for the cooling requirements of blades in differing temperature and pressure environments.

Rotor with variable angle blades

Abstract: A support, actuation, and balancing structure for rotor blades in a variable blade angle axial flow fan, compressor or turbine as may be used in a turbojet or turbofan engine. The supporting structure may include a shaft attached to each rotor blade and restrained from outward radial travel, under high centrifugal loading, by the inwardly facing surfaces of two spaced apart discs. Actuation may be provided by at least one fluid powered piston which controls blade angulation through rotation of one disc member relative to the other. Centrifugally controlled balancing means may also be provided to insure a uniform flow condition through the blades by maintaining the blades in a stable position of angulation upon disengagement of the actuator. Each rotor blade preferably includes a central axis about which the blade angle is varied, and which is in close proximity to the intersection of the leading edge of the blade with the blade tip.

Cooled jet flap vane

Abstract: A high temperature gas turbine diverts air compressed by the compressor of the engine for cooling the turbine nozzle vanes. These vanes have laminated walls with passages through the walls for cooling the vane walls. The vanes also have slots adjacent the trailing edge for blowing air toward adjacent vanes to provide a jet flap effect and thus reduce the effective area of the nozzle. The air diverted from the compressor is controlled so as to direct all the air for cooling at maximum engine rating and to use some of the air for jet flap purposes and correspondingly reduce the cooling air at lower power operation of the engine.

Guide vanes for supersonic turbine blades

Abstract: Guide vanes are installed between blades of the last stage of blading of a large steam turbine to form converging-diverging openings to minimize losses in this portion of the turbine. The guide vanes are fastened to adjacent blades through a shroud ring and through a lashing ring to connect the blades in such a manner as to reduce vibration and allow thermal expansion of the rotating blade assembly.

Starting system for a gas-turbine installation

Abstract: A gas-turbine installation having a pressurized-air hot-gas generator in which a fuel is reacted with the pressurized air, has a high-pressure turbine-driven compressor and a low-pressure turbine-driven compressor in tandem to supply the compressed air for the gasifier, the turbines being operated by the expanding combustible gases from the gasifier. One or both of the turbines may be provided with electrical generators and/or with starting motors and a steam-generating cycle may be provided for operation by the heat of the combustible gases. The starting system of the invention includes a compressed-air reservoir adapted to be charged by one or both of the compressors during normal operation of the system and capable of stirring a volume of air under such pressure that, for starting the system, the gasifier may communicate with the reservoir to generate sufficient hot combustion gases to drive the turbine.

Standard Measurement of Aircraft Gas Turbine Engine Exhaust Smoke

Abstract: A standard system (equipment and procedures) for measuring smoke emitted by aircraft turbine engines has been developed. It has been adopted by several Federal Government agencies. In this paper, the system is explained and its accuracy defined. An experimentally determined relationship between the system’s parameters and true smoke density (weight of solids per unit volume) is presented and theoretically examined. The definition of smoke plume visibility in terms of the system’s parameters is also developed. This work led to the conclusion that aircraft turbine engine exhaust smoke is composed of two groups of particles: the very small, which are primarily responsible for visible obscuration, and larger particles, which may constitute as much as half of the total by weight, but do not appreciably contribute to plume visibility.Copyright © 1971 by ASME

Flexible airfoil for compressor

Abstract: The inlet guide vanes for a turbine compressor are constructed of thin flexible material and mounted in a manner to be selectably formed into a desirable airfoil shape and camber angle by suitable control means.

Low pressure end diffuser for axial flow elastic fluid turbines

Abstract: An improved low pressure end diffuser for axial flow elastic fluid turbines, such as steam turbines, is disclosed. A housing is provided on the outer fairing member of the diffuser, which housing defines a vented chamber. The outer fairing member is provided with openings communicating between the chamber and the annular area within the turbine casing adjacent the leading edges of the last stage turbine blades. Injection slots are formed in the outer fairing member to communicate between the chamber and the exhaust outlet downstream of the trailing edges of the last stage turbine blades. The injection slots are formed in such a manner that the fluid will flow from the chamber along a major portion of the inner surface of the outer fairing member whereby fluid boundary layer on the fairing surface will be accelerated to prevent separation of the boundary layer from the surface thereby resulting in improved diffuser performance.