Showing papers on "Turbine published in 1968"

System and method for providing steam turbine operation with improved dynamics

Abstract: A PROGRAMMED DIGITAL COMPUTER CONTROL SYSTEM FOR AN ELECTRIC POWER PLANT STEAM TURBINE RESPONDS TO TURBINE IMPULSE CHAMBER STEAM TEMPERATURE AND OTHER INPUT VARIABLES TO CONTROL TURBINE INLET STEAM FLOW WITHIN CONSTRAINT LIMITS THAT PREVENT EXCESSIVE ROTOR LOADING AND ALLOW CONTROLLED ACCUMULATION OF TURBINE ROTOR PLASTIC STRAIN FATIGUE ACCORDING TO PREDETERMINED FATIGUE ACCUMULATION STANDARDS.

Method and apparatus for producing refrigeration

Abstract: Refrigeration system including a multi-stage compressor and two work expansion engines of the turbine type with the impellers of the expansion engines and the impeller of the final stage of the compressor being mounted on a common shaft. The work developed in the expansion engines provides the total power required for the final stage of the compressor and the final stage of the compressor provides the pressurized gas expanded in both expansion engines.

Film cooling of structural members in gas turbine engines

Abstract: 1,271,819. Turbine and like blades. GENERAL ELECTRIC CO. Sept, 19. 1969 [Sept. 27, 1968], No.46220/69. Heading F1T. A gas turbine or compressor blade 24 or other member has a common chamber 42 supplying cooling air through passages 51, 53, 54 to effect film cooling of the external surfaces of the member. Since the convex surface 60 is subject to a lower static pressure than the concave surface 58 each passage 54 has a portion 64 of increased crosssectional area adjacent surface 60 to reduce the excessive coolant flow velocity which would otherwise result. The portions 62, 64 of passage 54 may be of circular, elliptical or rectangular cross-sections and the passages may be inclined in a radial direction. The blade 24 also includes chamber 40 inter-connected by passages 48 and supplied with coolant from further passages (46), Fig. 2 (not shown), in the blade root. Passages 50 cool the trailing edge 52.

Gas turbine power plants having axialflow compressors incorporating contrarotating rotors

Abstract: 1,233,718. Gas turbine ducted fan engines; driving compressors. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec. 11, 1968 [Dec. 14, 1967], No.59031/68. Headings F1C, F1G and F1J. A gas turbine engine comprises an axial-flow compressor and a turbine, the compressor being divided into n co-axial units where n is two or more, each compressor unit comprising two contra-rotating rotors, and the turbine comprises (n+1) independent rotors each driving a transmission shaft, the turbine rotating in opposite directions considered from one to the next, each turbine rotor driving two rotors of two successive compressors, except for the first and last turbine rotors which each drive only one compressor rotor. In the gas turbine ducted fan engine shown in Fig. 1 the axial flow compressor assembly 7 comprises an L. P. contra-rotating compressor 11 and an H.P. contra-rotating compressor 12 and the turbine assembly 9 comprises three independent turbine rotors 13, 14, 15 each driving a shaft 26, 27, 28. The engine comprises also a ducted fan 2 upstream of the L.P. compressor. The H. P. turbine 13 is connected by shaft 26 to drive the inner rotors 22, 24 of the H.P. compressor. The L. P. turbine 15 is connected by shaft 28 to drive the outer rotor 19, 21 of the L. P. compressor, also the ducted fan 2. The I, P, turbine 14 is connected by shaft 27 and the shaft 27a which are inter-connected by spline coupling 31, to drive the inner rotor 18, 20 of the L. P. compressor also the outer rotor 23, 25 of the H, P, compressor. The bearings for the shafts are indicated diagramatically. The ducted fan engine shown in Fig. 2 again comprises three turbine stages 13, 14, 15 and two contra-rotating compressor stages 11, 12 but in this case the H. P. compressor does not comprise a rotatable outer drum or casing. The H. P. turbine 13 drives through shaft 26 an internal ring gear 58 which drives a gear 56 which in turn drives a shaft 49 carrying gears 48 which engage internal ring gears 49 carried by the compressor discs 42 which in turn carry blades 40. The L. P turbine 15 drives through shaft 28 the outer rotor 19, 21 of the L. P. compressor also the ducted fan 2. The I. P. turbine 14 drives through shaft 27 the inner rotor 18, 20 of the L. P. compressor, also through gearing 59, 57 shaft 53 and gearing 52, 47 the discs 43 and blades 41 of the I. P. compressor. In the assembly three gears 56 engage with the internal ring gear 58 each gear 56 driving a shaft 49 and gears 48; similarly three gears 57 engage the internal ring gear 59 each gear 57 driving a shaft 53 and gears 52.

Turbine stator cooling control

Abstract: The stator of a gas turbine includes an arrangement for controlling flow of cooling air to the vanes of the second stage turbine nozzle from the engine compressor. Control is by a valve defined by two rings extending around the exterior of the turbine nozzle which have different coefficients of thermal expansion so that the gap between them varies in accordance primarily with the temperature of the cooling air which tends to increase with the power output of the engine and thus with the need for cooling air.

Gas turbine engine with combustion chamber bypass for fuel-air ratio control and turbine cooling

Abstract: A gas turbine engine which may otherwise be of conventional configuration, single or plural shaft, regenerative or nonregenerative, is provided with a controlled bypass from the compressor to the turbine bypassing the combustion apparatus. Flow through this bypass is controlled so as to maintain the fuel-air ratio in the combustion chamber substantially constant notwithstanding variations in fuel flow and airflow with the load carried by the engine. Control of flow through the bypass may respond to setting of the fuel control device, to compressor discharge pressure, or to burner outlet temperature.

Velocity profiles and pumping capacities for turbine type impellers

Abstract: Velocity and angle profiles emanated by turbine type impellers were measured in both air and water using a hot wire anemometer probe and two and three dimensional pitot tubes. Pumping capacities were then calculated from the velocity data. The effect of the rotational speed and the dimensions of the turbine was investigated. On a mesure dans l'air et l'eau les profils de velocite et d'angle produits par une turbine a ailettes, en utilisant une sonde d'anemometre a fil chaud ainsi que des tubes de Pitot a deux ou trois dimensions. On a ensuite calcule les capacites de pom page a partir des resultats de velocite obtenus. On a egalement etudie l'effet de la vitesse rotative et des dimensions de la turbine.

Gas turbine assembly having low-pressure groups and high-pressure groups adapted to be selectively connected either in series or in parallel

Abstract: A gas turbine installation which includes a combustion chamber, a compressor unit supplying the combustion chamber and having a low-pressure compressor and a high-pressure compressor, a drive turbine unit driven by the combustion gases and driving the compressor unit, and an output engine driven by the combustion gases, in particular an output turbine, whereby the low-pressure compressor and high-pressure compressor are adapted to be connected either in series or in parallel.

Labyrinth seal for axial flow fluid machines

Abstract: A sealing device in a turbine for preventing excessive leakage of motive fluid between a stator and the tips of rotor blades, the leakage being from a high-pressure side to a low-pressure side, including an airfoil provided on the outer periphery of each rotor blade with the airfoil being skewed to pump the leakage fluid back to the high-pressure side.

Oxides of Nitrogen from Gas Turbines

Abstract: Experimental and theoretical studies were made to provide information on nitrogen oxide concentrations produced by gas turbine engines. Nitric oxide concentrations of from 100 to 350 ppm, adjusted to stoichiometric conditions, were measured in aircraft turbojet engines. Concentrations of less than 50 ppm, similarly adjusted, were measured in a 60 hp industrial gas turbine. Concentrations of about 100 ppm, also adjusted, were measured in a laboratory combustor of a design similar to gas turbine combustors. Carbon monoxide and unburned hydrocarbon concentrations also were determined. Comparison with predicted equilibrium concentrations shows strong departures from equilibrium.

System and method for operating a boiling water reactor-steam turbine plant

Abstract: A turbine follow control system for a boiling water reactorsteam turbine plant includes an electrical reference system which determines the reactor operating level through a reactor control system. The turbine follow control system operates turbine steam valves and steam bypass valves electrohydraulically to control the stem throttle pressure as the level of reactor operation is controllably varied to produce required steam flow. In another arrangement, a coordinated control system for a boiling water reactor-steam turbine plant includes an electrical reference system which simultaneously determines the reactor operating level and the turbine steam flow subject to throttle pressure control constraints.

Unit of propulsion by hydrodynamic reaction

Abstract: The improved unit of propulsion by hydrodynamic reaction consists of an integral turbine which has a pair of adjacent, counterrotating rotors, driven either by one motor through suitable gearings, or by two separate motors. The casing which encloses this counterrotating turbine ends in a nozzle. A conical or bullet shaped element provided with one or two baffles is housed in the casing between the second rotor and the nozzle and directs the jet towards the said nozzle which has movable sidewalls for regulating the outlet.

Turbine cooling construction

Abstract: A turbine cooling construction for use in a gas turbine engine which permits the use of stoichiometric temperatures within the turbine More specifically, an inlet turbine temperature in excess of 3,000* F may be utilized

The Heat Transfer Performance of Porous Gas Turbine Blades

Abstract: It is well known that the performance of the practical gas turbine cycle, in which compression and expansion are non-isentropic, is critically dependent upon the maximum temperature of the working fluid. In engines in which shaft-power is produced the thermal efficiency and the specific power output rise steadily as the turbine inlet temperature is increased. In jet engines, in which the gas turbine has so far found its greatest success, similar advantages of high temperature operation accrue, more particularly as aircraft speeds increase to utilise the higher resultant jet velocities. Even in high by-pass ratio engines, designed specifically to reduce jet efflux velocities for application to lower speed aircraft, overall engine performance responds very favourably to increased turbine inlet temperatures, in which, moreover, these more severe operating conditions apply continuously during flight, and not only at maximum power as with more conventional cycles.

Power plant for a helicopter

Abstract: 1,120,658. Helicopters. ROLLS-ROYCE Ltd. 20 April, 1967, No. 18300/67. Headings B7G and B7W. [Also in Division F1] A power plant for a helicopter comprises a gas turbine engine having a free turbine, a shaft drivingly connected to a fan (which may be a propeller), mechanical drive means for mechanically rotating a helicopter rotor, and speedsensitive clutch means for transmitting drive from the free turbine either to the mechanical drive means or to the shaft in dependence upon whether the rotational speed of the free turbine is respectively below or above a predetermined value. The engine shown is of the two-spool type comprising LP compressor 31, HP compressor 32, combustion equipment 33, HP turbine 34, LP turbine 35 and a separate power turbine 36, the HP turbine being connected to the HP compressor by means of shaft 40 and the LP turbine being connected to the LP compressor by means of shaft 41. The LP rotor assembly including shaft 41 is connected at its forward end to a shaft 42 which is connected through reduction gearing 44 to a ducted fan assembly 43 comprising fan blades 45 disposed in duct 47, the duct being supported by means of struts 50, 51. The power turbine 36 is connected to drive a helicopter rotor by means of shaft 53, gearing 55, shaft 54, speed-sensitive unidirectional clutch 60 and shaft 20. The power turbine is also connected to drive the ducted fan 43 by means of speed-sensitive unidirectional clutch 61 and shaft 41 of the LP rotor assembly, the arrangement being such that the clutch 60 is engaged when the speed of the power turbine is below a predetermined value so that the lift rotor is driven. When the aircraft reaches the required altitude, the pitch of the lift rotor blades is reduced so that the speed of the shaft 20 will tend to increase so that the clutch 60 becomes disengaged. The clutch 61 now becomes engaged as a result of the increased speed of the power turbine and the power turbine will now drive the fan 43. The fan was previously being driven by the LP rotor assembly but the fan blades were in fine pitch. In forward flight the lift rotor will auto-rotate, the aircraft being also provided with fixed wings to provide lift during forward flight. The helicopter shown comprises two lift rotors 11, 12 and two engines 22, 23, the engines being connected by shafts 20, 21 to a gear-box 17, the lift rotors being connected to the gear-box 17 by shafts 14, 16, 13. The fixed wings are shown at 26, 27.

Sealing system for turbine and compressor bearings

Abstract: In turbines and compressors, leakage of oil from a bearing chamber into gas passages and leakage of gas into the bearing chamber is prevented by evacuating the bearing chamber to draw a stream of air in one direction past a labyrinthine packing toward the bearing chamber, while drawing a stream of air from the same source past a second labyrinthine packing toward the gas passage by taking advantage of the vacuum-producing effect of the flow of gas.

Power conversion system operating on closed rankine cycle

Abstract: THE DISCLOSURE CONCERNS A POWER CONVERSION SYSTEM FOR CONVERTING HEAT ENERGY TO ELECTRICAL POWER, WHEREIN THE POWER CONVERSION SYSTEM INCLUDES A SO-CALLED JET CONDENSER CONNECTED TO THE EXHAUST OUTLET OF A TURBINE WHICH DRIVES AN ELECTRIC GENERATOR, SUCH AS AN ALTERNATOR, IN PRODUCING ELECTRICAL POWER. THE POWER CONVERSION SYSTEM COMPRISES A CLOSED RANKINE CYCLE EMPLOYING AN ORGANIC WORKING FLUID. THE SINGLE WORKING FLUID AFTER BEING HEATED TO ITS VAPORIZED PHASE DRIVES THE TURBINE TO GENERATE ELECTRICAL POWER AND IS DISCHARGED FROM THE EXHAUST OUTLET OF THE TURBINE IN ITS VAPOR PHASE FOR ADMISSION INTO THE CONDENSER. A JET STREAM OF COOLED WORKING FLUID IN ITS LIQUID PHASE IS INJECTED INTO THE JET CONDENSER TO MIX WITH THE VAPORIZED WORKING FLUID COMING FROM THE EXHAUST OUTLET OF THE TURBINE. THE MIXING OF THE COOLED LIQUID WORKING FLUID WITH THE VAPORIZED WORKING FLUID CAUSES RAPIE CONDENSATION OF THE VAPORIZED WORKING FLUID FOR REUSE IN THE SYSTEM CYCLE, WHILE PROVIDING FOR A REDUCTION IN THE TURBINE BACK PRESSURES WHICH ARE CRITICAL TO THE EFFICIENCY OF THE SYSTEM SO AS TO IMPROVE ITS EFFICIENCY IN PRODUCING AN ELECTRICAL OUTPUT FROM A SUITABLE HEAT SOURCE. THE HEAT SOURCE EMPLOYED WITH THE SYSTEM MAY COMPRISE NUCLEAR ENERGY, SUCH AS HEAT ENERGY FROM NUCLEAR REACTORS OR RADIOACTIVE ISOTOPES, OR CHEMICAL HEATING, SOLAR ENERGY, OR OTHER HEAT SOURCES WHICH ARE CAPABLE OF HEATING A WORKING FLUID IN ITS LIQUID PHASE IN A BOILER PRIOR TO ADMITTING THE WORKING FLUID AS A HEATED VAPOR INTO THE TURBINE FOR DRIVING THE TURBINE BLADES AND PRODUCING ELECTRICAL ENERGY THROUGH AN ALTERNATOR OPERATED BY THE ROTATING SHAFT OF THE TURBINE.

Cold-air investigation of a turbine for high- temperature-engine application. 3 - Overall stage performance

Abstract: Overall performance of stator component of cold air turbine determined for application to high temperature engine design

Pulse sensitive turbine nozzle

Abstract: A RADIAL INFLOW TURBINE EFFECTIVE TO RECOVER BLOWDOWN ENERGY FROM THE EXHAUST PORTS OF AN INTERNAL COMBUSTION ENGINE WHICH HAS TWO MANIFOLDS FEEDING FROM THE EXHAUST PORTS TO THE TURBINE HOUSING, THE HOUSING HAVING AN INLET THROAT DIVIDED BY A WALL ONLY THROUGH THE EFFECTIVE NOZZLE AREA TO A POINT WHERE EXHAUST GASES HAVE BEEN ACCELERATED TO A MAXIMUM TANGENTIAL VELOCITY PRIOR TO ENTRY INTO THE TURBINE WHEEL, THE HOUSING THEREAFTER HAVING AN UNDIVIDED SINGLE CIRCUMFERENTIAL GAS FLOW CHAMBER SIZED TO PROVIDE UNIFORM DISTRIBUTION AT CONSTANT TANGENTIAL VELOCITY TO THE TURBINE VANES.

Considerations of turbine cooling systems for Mach 3 flight

Abstract: Approximate average midspan metal temperatures and coolant flow requirements for turbine airfoils cooled by compressor exit bleed air

Combined plant installation for producing electrical power and fresh water from brine

Abstract: COMBINED INSTALLATION FOR THE PRODUCTION OF FRESH WATER AND ELECTRICITY COMPRISES AN ELECTRICAL GENERATOR UNIT WHICH PRODUCES ELECTRIC POWER FROM HEAT ENERGY SUCH AS A STEAM TURBINE. THE TURBINE ALSO DRIVES THE COMPRESSOR UNIT OF A COMPRESSION-EVAPORATOR PRODUCING FRESH WATER FROM BRINE AND THE HEAT REJECTED BY THE ELECTRICAL GENERATOR UNIT IS UTILIZED IN AN EVAPORATOR-DISTILLER LIKEWISE PRODUCING FRESH WATER FROM BRINE SUPPLED TO IT.