Showing papers on "Ram air turbine published in 1984"

Energy Efficient Engine high pressure turbine component test performance report

Abstract: The high pressure turbine for the General Electric Energy Efficient Engine is a two stage design of moderate loading. Results of detailed system studies led to selection of this configuration as the most appropriate in meeting the efficiency goals of the component development program. To verify the design features of the high pressure turbine, a full scale warm air turbine test rig with cooling flows simulated was run. Prior to this testing, an annular cascade test was run to select vane unguided turn for the first stage nozzle. Results of this test showed that the base configuration exceeded the lower unguided turning configuration by 0.48 percent in vane kinetic energy efficiency. The air turbine test program, consisting of extensive mapping and cooling flow variation as well as design point evaluation, demonstrated a design point efficiency level of 90.0 percent based on the thermodynamic definition. In terms of General Electric cycle definition, this efficiency was 92.5 percent. Based on this test, it is concluded that efficiency goals for the Flight Propulsion System were met.

Gas turbine engine active clearance control

Abstract: Method for controlling the clearance between rotating and stationary components of a gas turbine engine are disclosed. Techniques for achieving close correspondence between the radial position of rotor blade tips and the circumscribing outer air seals are disclosed. In one embodiment turbine case temperature modifying air is provided in flow rate, pressure and temperature varied as a function of engine operating condition. The modifying air is scheduled from a modulating and mixing valve supplied with dual source compressor air. One source supplies relatively low pressure, low temperature air and the other source supplies relatively high pressure, high temperature air. After the air has been used for the active clearance control (cooling the high pressure turbine case) it is then used for cooling the structure that supports the outer air seal and other high pressure turbine component parts.

On the Theory of the Wells Turbine

Abstract: Presentation d'une etude theorique du comportement thermodynamique de la turbine de Wells, turbine a ecoulement axial adaptee a l'extraction d'energie a partir d'un ecoulement d'air alternatif. Developpement d'une analyse bidimensionnelle, et obtention d'expressions pour la forme d'ailette rendant maximal le rendement de la turbine. Analyse tridimensionnelle montrant que des distorsions radiales importantes du profil de vitesse axial peuvent se produire en fonction de la forme de l'ailette

Steam-injected free-turbine-type gas turbine.

Abstract: A steam-injected free-turbine type of gas turbine is disclosed In order to avoid the necessity of redesigning the compressor/core turbine, the shaft of the core turbine is modified to provide additional load output As steam is injected into the system the resulting excess power of the core turbine is taken out of the system by coupling the compressor output shaft with a load Thus, the core turbine operates as a single shaft turbine in addition to the existing power turbine A control provides control of the load output of the two turbine output shafts so that the compressor/turbine stays in the matched operating domain

Turbine power plant system

Abstract: A turbine power plant system consisting of three sub-systems; a gas turbine sub-system, an exhaust turbine sub-system, and a steam turbine sub-system. The three turbine sub-systems use one external fuel source which is used to drive the turbine of the gas turbine sub-system. Hot exhaust fluid from the gas turbine sub-system is used to drive the turbines of the exhaust turbine sub-system and heat energy from the combustion chamber of the gas turbine sub-system is used to drive the turbine of the steam turbine sub-system. Each sub-system has a generator. In the gas turbine sub-system, air flows through several compressors and a combustion chamber and drives the gas turbine. In the exhaust turbine sub-system, hot exhaust fluid from the gas turbine sub-system flows into the second passageway arrangement of first and fourth heat exchangers and thus transfering the heat energy to the first passageway arrangement of the first and fourth heat exchangers which are connected to the inlets of first and second turbines, thus driving them. Each turbine has its own closed loop fluid cycle which consists of the turbine and three heat exchangers and which uses a fluid which boils at low temperatures. A cooler is connected to a corresponding compressor which forms another closed loop system and is used to cool the exhaust fluid from each of the two above mentioned turbines. In the steam turbine sub-system, hot fluid is used to drive the steam turbine and then it flows through a fluid duct, to a first compressor, the first fluid passageway arrangement of first and second heat exchangers, the second passageway of the first heat exchanger, the combustion chamber of the gas turbine where it receives heat energy, and then finally to the inlet of the steam turbine, all in one closed loop fluid cycle. A cooler is connected to the second passageway of the second heat exchanger in a closed loop fluid cycle, which is used to cool the turbine exhaust.

Ram air turbine hydraulic power system

Abstract: A ram air turbine hydraulic power system and pressure compensator valve (24) usable therein for controlling the displacement of a variable displacement pump (12) driven by a ram air turbine (10). The pressure compensator valve has a valve member (42) with a pilot responsive to discharge pressure of the pump and a compensator spring (50) acting on the valve member in opposition to the discharge pressure, a movable control piston (54) engaging the compensator spring, a pair of control springs (70, 72) engaging said control piston and acting in opposition to each other, and a control pressure which is proportional to the square of pump speed is applied to the control piston whereby the force of the compensator spring is varied depending upon the position of the control piston.

Air powered electrical vehicle

Abstract: The invention is a method of producing electrical power in situ for use in the propelling of a moving vehicle through an air passage. This is achieved by streamlining the air of the air passage, then channelling the air through into a small cross-sectional area, by appropriate design of the vehicle, so that the air is accelerated to a relatively high velocity, substantially increased over that of the moving vehicle. The forward kinetic energy of the air stream is therefore increased in accordance with Bernoulli's theorem and is therefore capable of producing sufficient energy to not only overcome the air resistance of the vehicle but also most of the other drains on the power consumption of the vehicle, such as frictional forces. The kinetic energy of the air stream so induced is harnessed by placing an air turbine system in the path of the air stream, in an optimised position towards the rear of the vehicle. A generator is connected to the air turbine and the electric energy produced is fed to an electric motor, which propels the vehicle. This electrical energy could either be fed directly to the motor or first be transferred to a battery storage system. Whilst there are a number of air turbine systems that could be employed with this invention a special dual turbine arrangement is described in the request specification.

Remote control of the power control device of a vacuum cleaner air turbine

Abstract: The invention relates to a remote control of the power control device of a vacuum cleaner air turbine. The control possesses an actuating element (1, 31, 51) arranged on the handle of the suction pipe in order to influence a pressure switch (21) by whose diaphragm (22) contacts are actuated which in turn are connected to elements of the power control device. Both switching on and off, and a power control which is uninfluenced by the vacuum fluctuations which occur during vacuuming, are made possible by an arrangement wherein the pressure switch (21) can be optionally subjected to pulses of super-atmospheric or sub-atmospheric pressure by means of the actuating element (1, 31 or 51) and wherein, furthermore, at least one contact (25 and 26) respectively is arranged on each side of the diaphragm (22), one of these contacts being actuated in the event of a pulse of super-atmospheric pressure and the other in the event of a pulse of sub-atmospheric pressure.

The Wells turbine in an oscillating air flow

Abstract: An experimental study of the performance of a 0.2 m diameter Wells self rectifying air turbine with NACA 0021 blades is presented. Experiments were conducted in an oscillating flowrig. The effects of Reynolds number and Strouhal number on the performance of the turbine were investigated. Finally comparison between the results with the predictions from uni-directional flow tests are made.

Turbine-heat exchanger assembly

Abstract: A compact air cycle refrigeration system utilizes a three wheel air cycle cooling machine having a fan mounted between a turbine and compressor on a common drive shaft. The fan is positioned between two series-mounted heat exchangers mounted in a ram air duct and used to cool hot engine bleed air which drives the turbine. The turbine, in turn, drives the fan and the compressor, and the eingine bleed air is directed, via the compressor, through the heat exchangers and into the turbine.

Marine gas turbine power transmission

Abstract: A marine gas turbine engine including a fluid coupling between its low pressure turbine and power turbine. During forward drive the fluid coupling is drained so that the exhaust gases from the low pressure turbine drive the power drive in a first direction of rotation. For reverse drive, the fluid coupling is filled so as to couple the low pressure turbine and power turbine and cause the power turbine to rotate in the opposite direction of rotation. When the fluid coupling is operational, the compressor delivery air and low pressure turbine exhaust gases are exhausted to atmosphere.

The aerodynamic design and performance of the NASA/GE E3 low pressure turbine

Abstract: The aerodynamic design and scaled rig test results of the low pressure turbine (LPT) component for the NASA/General Electric Energy Efficient Engine (E3) are presented. The low pressure turbine is a highly loaded five-stage design featuring high outer wall slope, controlled vortex aerodynamics, low stage flow coefficient, and reduced clearances. An assessment of its performance has been made based on a series of scaled air turbine tests which were divided into two phases: Block I (March through August, 1979) and Block II (June through September, 1981). Results from the Block II five-stage test, summarized in the paper, indicate that the E3 LPT will attain an efficiency level of 91.5 percent at the Mach 0.8/35,000 ft. max. climb altitude design point. This is relative to program goals of 91.1 percent for the E3 demonstrator engine and 91.7 percent for a fully developed flight propulsion system LPT.

Charge air cooling for exhaust turbocharger

Abstract: The invention is intended, especially in the case of high-revving engines with turbochargers, to cool the compressed, hot charge air generated by the charge air turbine more strongly than occurs in radiators with airstream, the more strongly cooled charge air preventing self-ignition of the quantity of fuel fed to the cylinders earlier and more reliably and the increased quantity of cooling air passing by way of an air pressure fan, the fan impeller of which is fixed without any additional drive to the common turbine shaft between exhaust turbine and charge air turbine and rotates with the turbine shaft (n= 1,000,000 rpm), so that, for identical cooling rates, the cooling system with air pressure fan cooling can be designed with smaller dimensions than a cooling system with airstream cooling, thereby leading to fuel saving.

Electrostatic spray gun

Abstract: THE INVENTION CONCERNS AN ELECTROSTATIC SPRAY GUN WITH AIR TURBINE. THE GUN 10 HAS A HIGH VOLTAGE GENERATOR 52 DRIVEN BY AN AIR TURBINE 50 WHICH, SINCE ITSELF, IS DRIVEN BY COMPRESSED AIR WHICH FLOW IS CONTROLLED BY A VALVE 34 ACTUATED BY A RELAXATION 24. AIR FLOW IS LIMITED BY A REGULATOR 44. THE EXHAUST CIRCUIT OF THE AIR PASSES ON THE ELECTRICAL DEVICES OF THE GUN TO COOL. FIELD OF APPLICATION: ELECTROSTATIC PAINT SPRAY, ETC.

Apparatus and methods for monitoring inertia

Abstract: Inertia of a body e.g. a solids- liquid separating centrifuge (16) is monitored while in use so that extent of cake build-up can be inferred. Means is provided for maintaining constant rotational speed of the centrifuge bowl and then changing (reducing) the speed sharply. inertia of the centrifuge and hence cake build-up is deduced from a measurement of deceleration and power. The centrifuge is driven by an air turbine (21). Air is cut off to initiate deceleration. Turbine power is proportional to inlet pressure and measured on gauge 33. Deceleration is determined using a speed sensor 25 and an analogue differentiator.

Air cycle cooling machine

Abstract: © A compact air cycle refrigeration system utilizes a three wheel air cycle cooling machine having a fan mounted between a turbine and compressor on a common drive shaft. The fan is positioned between two series-mounted heat exchangers mounted in a ram air duct and used to cool hot engine bleed air which drives the turbine. The turbine, in turn, drives the fan and the compressor, and the engine bleed air is directed, via the compressor, through the heat exchangers and into the turbine.

Wave force power generator

Abstract: PURPOSE:To enhance the power generating capacity by driving a pump through the use of both wave force and wind force energies. CONSTITUTION:When the wave surface moves up and down, the volume in air chambers 2, 3 increases or decreases to cause air stream in an air duct 41 as shown by arrow, and thus the wave force energy is conducted to an air turbine 51. A pump 61 driven by this air turbine 51 pumps up the crude oil 19 in storage chamber 18 through a suction pipe 71 and discharge it to a tank 9. A wind wheel 10, which has got energy from the sea wind, will meanwhile drive another pump 11 so as to pump up the crude oil 19 also contained in said storage chamber 18 to the tank 9. Therefore the oil 19 is supplied in good correspondence to each air chamber, which ensures well increase of the power generating capacity.

Optimal Design of Kaimei-type Wave Power Absorber

Abstract: Japan Marine Sience and Technology Center is putting into practice th e Kaimei project Phase II. The targets of this plan mainly include the field test of the turbine and generator, and the establishment of the phase control technique. The wave power device Kaimei is classified as the floating attenuator type using the air turbine and the generator. The performance of this device seems to depend on the arrangement of the air chambers and the buoyancy rooms, and also on the external loads. This study as a part of the project aims to extablish the design procedure of the optimal device form by predicting the power output and estimating the feasibility at the identified site and sea condition.In this paper the hydrodynamic forces are calculated by the singular distribution method and the performance is estimated by changing the fundamental form parameters. The results are following.(1) The wave power absorbing performance of the Kaimei type device is almost proportional to the areal ratio of the air chambers in an optimal external load condition.(2) By making the breadth of the device wide, we can expect the increasing performance.Further in order to assure the design procedure, the model experiment was made and compared with the analysis. Both agree well as a whole. However, the heaving and pitching motions of the floating device are made clear to badly affect on the performance. The author recommends the device form hard to move, or with the performance not susceptible of the motion of the floating device.

Centrifugal oil mist separator for gas turbine

Abstract: PURPOSE:To reduce the amount of oil consumption by bleeding partially the air from the outlet of a compressor of a gas turbine, by allowing it to turn the blades in a certrifugal oil separator, and thereby collecting fine oil mist contained in the air in a great quantity. CONSTITUTION:At the bearing housing of a gas turbine on its centrifugal compressor side, the air at the outlet of the compressor is utilized for returning the oil to the gear box together with the air so as not to leak when the oil is sent to the bearing. Here the gear box is equipped with a centrifugal oil mist separator 27. In thie separator 27, a circular wire brush 29 is hung on a shaft 30 in a cylinder 28, and this shaft 30 is so arranged as capable of being driven by an air turbine 22 furnished outside the body 28. The brush 29 is rotated at a high speed by the air turbine 22 by utilizing the air bled out of the exhaust hole of the compressor to give this air a swirl so as to spatter the oil attached to the brush 29 off to its surrounding.

Output power boost system utilizing pneumatic energy

Abstract: PURPOSE:To effectively utilize natural energy, by providing such a system that heat which is generated when an air-compressor is driven and is accumulated as heat energy, is made contact, a several time, with compressed air whose heat is absorbed and which is accumulated as cooled compressed air, so that an output power is obtained. CONSTITUTION:In a pneumatic circuit 10, high temperature and high pressure air compressed by a compressor 12 which is driven by wind power and water power, lowers its temperature under adiabatic expansion after giving its heat to heat medium in heat-exchangers 13, 14, and is accumulated as cooled compressed air. Heat recovered by the heat-exchangers is circulated in a heat medium circuit 20 by means of a heat medium compressor 21, to utilize, in one part, for heating water and, in the remaining part, for heating and pressure-boosting compressed air for working in an air heat turbine 40. In a boiling water circuit 30, hot water in a hot water storage tank 22 is fed to the air turbine 40 through an ejector 31 and then is recirculated to the hot water storage tank 22. With this arrangement natural energy may be effectively utilized.

Turbine casing for tandem air turbine

Abstract: PURPOSE:To aim at improvements in turbine efficiency, by installing a partition wall, bisecting the inside of a turbine casing, in position between two air turbines being set up symmetrically, while making each of air passages to these air turbines independent and thereby preventing the occurrence of turbulence in an airflow. CONSTITUTION:A generator 4 is placed on an air chamber 1, and two Wells turbines 61 and 6b are attached symmetrically to the shaft 5. In addition, a turbine casing 8 housing the generator 4 and these Wells turbines 6a and 6b is set up on top of the air chamber 1. The inside of this casing 8 is bisected by a partition wall 9 set up in a spot of the generator 4, forming two independent airflow passages 10a and 10b. With this constitution, air turbulence attributable to a collision of air flowing in from these airflow passages 10a and 10b at both sides is prevented from occurring, thus turbine efficiency is exceptionally improved.

Performance prediction of the Wells self-rectifying air turbine

Abstract: An experimental and analytical study of the effects of geometric and aerodynamic variables on the performance of the Wells self-rectifying axial flow air turbine is presented. Experiments were performed in a unidirectional flow rig. Two approaches to the predictions of the performance of the Wells turbine were described, both of which were based on twodimensional cascade theory and isolated aerofoil data. Finally, comparisons of the predicted results with the experimental results were made.