Showing papers on "Gas compressor published in 1969"

The Response of Axial Flow Compressors to Intake Flow Distortion

Abstract: The response of a lift engine model compressor to inlet pressure distortion is studied in detail to determine the nature and extent of the critical area of spoiling. This is found to be a sector of width between 60 and 90 deg. On this basis a simple distortion index is proposed which implies that only the circumferential pressure gradients of a complex distortion pattern are significant. The “Parallel Compressor” model satisfactorily explains surge and this experience is related to different types of compressors and to complex spoiling patterns. Comments are made on the differences in behavior between compressors operating on rig test and in engines.Copyright © 1969 by ASME

Gas turbine power plant

Abstract: A TURBO-FAN POWER PLANT IS DISCLOSED IN WHICH THEY ARE TWO INDEPENDENT FANS IN THE FAN DUCT RESPECTIVELY DRIVEN BY A GAS GENERATOR AND AN INDEPENDENT FREE TURBINE. THE GAS GENERATOR INCLUDES IN AXIAL FLOW SERIES LOW, INTERMEDATE AND HIGH PRESSURE COMPRESSOR RESPECTIVELY DRIVINGLY INTERCONNECTED WITH HIGH, INTERMEDIATE AND LOW PRESSURE TURBINES, THE INTERMEDIATE PRESSURE TURBINE BEING DRIVING- LY CONNECTED TO THE UPSTREAM OR FRONT OF THE TWO FAN THE DRIVE ARRANGEMENT OF THE FANS AND THEIR AXIAL SPACING ENABLES THEM TO ROTATE AT RELATIVELY LOW SPEEDS AND SUB STANTALLY WITHOUT ANY WAKE INTERACTION THEREBETWEEN , WHEREBY THE OVERALL NOISE OF THE POWER PLANT IS REDUCED.

Gas turbine engine power plants

Abstract: A closed-cycle gas turbine engine power plant employing a nuclear reactor to heat its working fluid, helium, is provided with a bypass valve whereby a variable amount of the helium compressed by the compressor or compressors may be caused to bypass the nuclear reactor and flow directly to the inlet of the turbine or turbines, thus enabling the turbine inlet temperature, and therefore the power output of the power plat, to be varied much more quickly than can be achieved by varying the heat output of the nuclear reactor.

Gas turbine engine constant speed thrust modulation

Abstract: A device is shown for modulating the thrust output of a gas turbine engine without the necessity of varying the speed of said engine. The device includes means for bypassing a portion of the compressor discharge air to a manifold surrounding the engine tail pipe, and, as required, to the turbine cooling flowpath for the purpose of transiently augmenting turbine cooling flow. The manifold is provided with a plurality of swirl inducing nozzles having inlets in fluidic flow cooperation with the manifold and outlets in fluidic flow cooperation with the tail pipe such that bypass flow is provided to the tail pipe in such a manner as to induce swirl within the main gas stream thereby significantly increasing tail pipe pressure losses and thus reducing thrust output of the engine. Engine speed may be maintained during operation of this device and delay time between increased thrust demand and actual thrust output are thereby lessened.

Bypass engine with afterburning and compressor bleed air heat exchanger in bypass duct

Abstract: 1,239,366. Gas turbine by-pass jet engines. GENERAL MOTORS CORP. Feb. 26, 1970 [April 16, 1969], No. 9263/90. Headings F1G and F1J. The invention relates to a gas turbine jet engine of the by-pass type in which combustion equipment is provided in the by-pass duct, a heat exchanger also being disposed in the by-pass duct upstream of the duct burners, there being means for bleeding hot air from the engine compressor and passing it through the heat exchanger so as to cool the bleed air and to pre-heat the by-pass air, the cooled bleed air being utilized for turbine cooling; combustion in the duct burners is improved by the pre-heating of the by-pass air. The engine shown comprises LP compressor 9, HP compressor 15, combustion equipment 17, HP turbine 18 and LP turbine 19. A portion of air from the LP compressor 9 passes through by-pass duct 10 discharging through outlet 21 into the chamber 23; the turbine exhaust gases discharge through outlet 22 into chamber 23, the combined flows discharging through propulsion nozzle 7. Combustion equipment in the form of duct burners 30 is disposed in the by-pass duct 10. Reheat equipment 27, 29 is disposed in the outlet duct from the turbines 18, 19. A heat exchanger 35 is disposed in the by-pass duct and comprises a series of longitudinally-extending tubes 45 extending between an inlet header 37 and an outlet header 39. Air from the HP compressor is tapped off at 43 and passed through duct 42 to the inlet header 37. The air is cooled in flowing through the tubes 45 and the cooled air passes from the outlet header 39 through the ducts 46, 49 and is subsequently utilized for cooling purposes not shown. The by-pass air flowing through the duct 10 is pre-heated indirectly by the heat exchanger 35 and the combustion at the duct burners 30 is thereby improved.

Cooling of turbine rotors in gas turbine engines

Abstract: THE DISCLOSURE SHOWS A GAS TURBINE ENGINE HAVING A COMPRESSOR, COMBUSTOR, AND TURBINE SEQUENTIALLY ARRANGED. A ROTATING, AIR ENTRY CHAMBER IS FORMED AT THE BASE OF THE TANGS OF TURBINE BUCKETS, WHICH PROJECT FROM THE TURBINE ROTOR INTO THE HOT GAS STREAM FROM TEH COMBUSTOR. A RELATIVELY STATIONARY, ANNULAR NOZZLE FORMS THE ENTRANCE TO THIS ROTATING CHAMBER. AIR IS DUCTED FROM THE DISCHARGE OF THE COMPRESSOR TO THIS NOZZLE. THE NOZZLE IS PROVIDED WITH VANES WHICH ACCELERATE THE COMPRESSOR DISCHARGE AIR INTO THE ROTATING CHAMBER WHICH IS AT A LOWER PRESSURE. THE NOZZLE IMPARTS, TO THE COOLING AIR, A VELOCITY VECTOR HAVING A COMPONENT RELATIVE TO THE ROTATING CHAMBER (AND TURBINE ROTOR), WHICH IS GENERALLY AXIAL. THE AIR IS REDUCED IN STATIC TEMPERATURE, AS IT IS ACCELERATED THROUGH THE NOZZLE, AND ENERGY LOSSES ARE MINIMIZED DUE TO THE VELOCITY VECTOR OF THE COOLING AIR BEING ESSENTIALLY AXIAL RELATIVE TO OPENINGS IN THE TURBINE ROTOR, WHICH THE AIR ENTERS TO FLOW THROUGH PASSAGEWAYS PROVIDING AN INTERNAL COOLING MECHANISM FOR THE TURBINE BUCKETS.

Gas turbine unit for generating mechanical energy and compressed air

Abstract: A gas turbine aggregate, especially an auxiliary unit for aircrafts which is intended to produce both mechanical energy and compressed air for loads, and in which a line branching off from the compressed air line that is supplied with compressed air from the compressor, leads to an air turbine which, in its turn, is connected with the output shaft of the gas turbine either directly or indirectly; the branch line from the compressed air line to the air turbine is provided with a valve to enable selective opening and closing of the branch line.

Turbine engine having multistage compressor with interstage bleed air system

Abstract: A bleed system which provides air for other than combustion purposes in a gas turbine engine. Bleed air is diverted from a multistage axial flow compressor through a diffuser flow passageway formed in the casing of the compressor. The entrance to this bleed passageway is defined by an annular lip disposed, in an axial sense, between a row of stator vanes and a row of rotor blades.

Mobile refrigeration system

Abstract: The compressor and evaporator and condenser fans of a mobile refrigeration system are driven by a continuously operating internal combustion engine. Temperature control of the refrigeration system when powered by the internal combustion engine is obtained by cycling the refrigeration system between heating and cooling cycles. A defrost cycle clutch is provided for disengaging the evaporator fan when the evaporator coil is defrosting. When an alternating current power source is available, the condenser fan and compressor may be driven by a standby electric motor, which is cycled off and on to obtain temperature control. A separate electric motor is provided to continuously drive the evaporator fan during this cycling of the standby electric motor. Means is provided to disengage the defrost clutch during operating of this separate electric motor. When the system is connected for standby motor operation, this separate electric motor is deenergized during the defrost cycle.

Refrigeration system oil separator

Abstract: An oil separator for use in a refrigeration system, having a plurality of compressors and evaporators, receives the discharge of refrigerant and oil separately from each compressor to separate the oil which is returned to the compressor from the refrigerant which is passed on to a condenser.

Refrigeration system with suction line accumulator

Abstract: A refrigerant accumulator in the suction line of a closed refrigeration system, provided with a controllably heated metering tube between the bottom of the accumulator and a downstream point in the suction line, to ensure at least adequate reevaporation of the refrigerant, to eliminate slugging and to return oil to the compressor, particularly during the hot gas defrosting portion of the refrigeration cycle, the heating being effected electrically or by means of hot gas from the compressor.

Oil equalization system

Abstract: A system for equalizing the level of the oil in each of a plurality of compressors in a refrigeration system wherein each compressor is provided with an oil level equalizer connected to a common oil line and means are provided for substantially uniformly distributing oil returning from the system to each of the compressors.

Ducted fan-jet engine

Abstract: A ducted fan-jet power plant in which a part of the bypass airflow supplied by the low-pressure compressor is conducted through hollow turbine discharge guide blades, open at their trailing edges, for the purpose of mixing the bypass flow and the main flow of the power plant within the area of the turbine discharge guide blades.

Receiver-separator unit for liquid injected gas compressor

Abstract: A combination gas receiver-liquid separator unit for use in a liquid injected gas compressor system The receiver-separator unit comprises an elongated cylindrical vessel having a transverse partition sealingly dividing the vessel into two separate compartments for separating liquid entrained in a flowing gas stream and for storing liquid-free gas under pressure A check valve interposed between compartments prevents the backflow of liquid-free gas into the separator compartment The separator compartment includes a primary inertial separation stage and secondary and tertiary impingement type separation stages The secondary and tertiary separation stages comprise a removable separator element The separator compartment also serves as a liquid reservoir for the associated gas compressor system

Apparatus for manufacturing high pressure inert gas

Abstract: THIS INVENTION RELATES TO AN APPARATUS FOR MANUFACTURING HIGH PRESSURE INERT GAS UTILIZING HYDROCARBON FUEL, THE GAS BEING PRODUCTED BY THE BURNING OF HYDROCARBON FUEL IN AN INTERNAL COMBUSTION ENGINE, THE EXHAUST GASES THEREFROM BEING CONVEYED THROUGH A CATALYTIC CONVERTER WHEREBY SUBSTANTIALLY INERT GAS A DERIVED THEREFROM, AND INCLUDING MEANS OF CONTROLLABLY RECYCLING SUCH INERT GAS THROUGH ENGINE DRIVEN COMPRESSOR STAGES TO VARY THE LOADING ON THE ENGINE AND THEREBY VARY THE INERT GAS OUTPUT IN RESPONSE TO THE DEMAND. AN ADDITIONAL EMBODIMENT OF THE INVENTION INCLUDES MEANS TO MAINTAIN A POSTIVE PRESSURE IN ALL PORTIONS OF THE SYSTEM, INCLUDING THE ENGINE ENHAUST MANIFOLD AND CATALYTIC CONVERTER, SO THAT ANY INADVERTENT LEAK IN THE SYSTEM WILL NOT RESULT IN AIR BEING DRAWN INTO THE SYSTEM.

Two-spool auxiliary power unit and control means

Abstract: A gas turbine engine with dual, telescoped, independently acting rotor constructions having a multistage, axial, low-pressure compressor impeller on one rotor and a single-stage, centrifugal, high-pressure impeller on the other rotor. Casing provides separated bleed air and combustion air chambers, the former receiving air from one impeller and the latter receiving highpressure air from the other. Control means are provided to cause one rotor to operate at constant speed and the other to operate at variable speeds necessary to meet predetermined pneumatic requirements with consequent maximum efficiency in all stages of operation whereby the lowest possible fuel consumption per mission will result.

Liquefaction of natural gas using separated pure components as refrigerants

Abstract: A gas liquefaction system wherein the refrigerant components are mixed with one another and, thereafter, separated into individual streams which enter the system as liquid streams. Cooling is produced by evaporating the cooled liquid component streams into a gas stream, which after all the individual cooled liquid component streams have been evaporated into it, forms the mixed refrigerant component stream returned to the compressor.

Mechanisms of Sand and Dust Erosion in Gas Turbine Engines

Abstract: : The experimental program is organized to evaluate the relative importance of erosion influencing variables introduced by the carrier gas, the dust suspension and the target materials themselves. Test conditions have been chosen to simulate the range of gas temperatures (RT - 800 F) static pressures (1 - 16 atmospheres) and gas and particle velocities (500-1500 fps) encountered in a typical high-performance compressor. The report includes: (1) a literature survey and data review, (2) an analysis of the physical environment in a typical high-performance compressor and the formulation of an erosion test program based on this environment, and (3) the execution of the erosion test program, including the design and construction of special test equipment. (Author)

Refrigeration system with multi-stage throttling

Abstract: A REFRIGERATING SYSTEM PROVIDED WITH MULTI-STAGE THROTTLING AND WITH A POSITIVE DISPLACEMENT COMPRESSOR OF THE ROTARY TYPE, THE CASING OF THE COMPRESSOR BEING PROVIDED BETWEEN ITS LOW PRESSURE AND HIGH PRESSURE PORTS WITH ONE OR MORE ADMISSION PORTS FOR INTERMEDIATE PRESSURE GAS FROM LIQUID SEPARATORS LOCATED BETWEEN THROTTLING POINTS. THE GAS FORMED DURING THROTTLING IS SUPPLIED THROUGH THESE ADMISSION PORTS TO THE WORKING COMPARTMENT OF THE COMPRESSOR. THE OPENING AND CLOSING OF THE ADMISSION PORTS IS ACHIEVED BY THE ACTION OF THE COMPRESSOR WHICH HAS ITS ROTOR LOBES OPERATIVE AS VALVES FOR THE ADMISSION PORTS.

Control for refrigeration system

Abstract: A control in a refrigeration system to control the rate of flow of refrigerant to the evaporator in response to variations in rate of flow of liquid refrigerant from the evaporator. A sump in the suction line between the evaporator and compressor for collecting liquid discharged with vapor from the evaporator. A pump for pumping liquid at a controlled rate from the sump for mixture with the vapor supplied from the upper end of the sump to the compressor. A liquid level sensor for sensing changes in the level of liquid within the sump and for controlling operation of an expansion valve on the inlet side of the evaporator in response to variations of liquid within the sump.

Central refrigeration system with automatic standby compressor capacity

Abstract: A central refrigeration system for supermarkets and the like requiring two or more temperature levels of refrigerated fixtures wherein separate compressors operate the fixtures at different temperature levels and with only one or two large compressors for each temperature level. The system employs a single condenserreceiver for the refrigerant discharged from all of the compressors and a single oil separator for returning oil to the compressors. A control arrangement responsive to an abnormal increase in the suction pressure on a given compressor automatically operates a valving arrangement to transfer at least a portion of the refrigerant load on that compressor to another compressor normally operating fixtures at a different temperature level.

Automotive air-conditioning system

Abstract: IN PREFERRED FORM, AN AUTOMOTIVE AIR-CONDITIONING SYSTEM HAVING A COMPRESSOR, A CONDENSER, AN EXPANSION VALVE, AN EVAPORATOR AND A FLOW REGULATING THROTTLING VALVE SERIALLY CONNECTED TOGETHER, RESPECTIVELY, AND INCLUDING AN EQUALIZER LINE BETWEEN THE EXPANSION VALVE AND THE THROTTLING VALVE OUTLET. THE EQUALIZER LINE IS NORMALLY BLOCKED BY A THERMALLY ACTUATED VALVE WHICH OPENS WHEN THE COMPRESSOR TEMPERATURE EXCEEDS A PREDETERMINED MAXIMUM. THE OPENING OF THE EQUALIZER LINE TRANSMITS COMPRESSOR INLET PRESSURE TO THE EXPANSION VALVE WHICH OPENS IT TO ALLOW REFRIGERANT TO FLOW THROUGH THE EVAPORATOR AND INTO THE COMPRESSOR FOR COOLING PURPOSES.

Sound suppressor for jet engine inlet

Abstract: An apparatus to suppress noise emitted in a forward direction from the compressor of an airplane jet engine, particularly for approach mode operation of the airplane. There are in the engine inlet two or more sets of vanes which extend transversely across the engine inlet at a location forward of the engine compressor. The sets of vanes can be translated axially with respect to one another. For low engine rotational speed the sets of vanes are positioned in generally the same transverse plane to provide a more restricted flow area in the inlet. This chokes flow in the inlet to cause the air in the inlet to flow at, or nearly at, sonic velocities in the region of the vanes. For higher engine speeds when greater air flow through the inlet is required, the two or more sets of vanes are translated axially with respect to one another to provide greater flow area through the inlet while maintaining the desired air velocity for noise attenuation.

Automatic compressor drain system

Abstract: Method and apparatus for automatically draining liquid condensate from a body of compressed gas wherein a condensate drain valve is automatically opened at stated intervals causing liquid to pass through a drain system which is provided with a sensing chamber inserted between a pair of orifices so that the pressure change accompanying the end of liquid flow and the beginning of gas flow can be employed to cause immediate closure of the drain valve with a minimum loss of air.

Compressors for gas turbine engines

Abstract: 1280113 Centrifugal and axial-flow compressors; gas turbine engines AVCO CORP 30 June 1970 [4 Aug 1969] 31621/70 Headings F1C and F1G A compressor in or for a gas turbine engine comprises an axial-flow section 32, 46, Fig. 1, and a downstream, contra-rotating mixed-flow section 62. The axial-flow section discharges air at subsonic absolute velocity. The mixed-flow section has an inlet portion which is of substantially constant flow area and receives the air at supersonic relative velocity to thereby produce shock waves and reduce supersonic flow to subsonic, whereafter the air is radially accelerated and diffused in the outlet portion of the mixed-flow section. The impeller blades of the latter may be divided into an inlet row and and outlet row separated by a row of stator blades, Fig. 3 (not shown). Stator vanes (150), Fig. 8 (not shown), may be located immediately upstream of the mixed-flow section to equalize the relative velocity of the entering air over the radial extent of the annular flow duct. In the gas turbine engine shown, the compressed air is discharged through a diffuser 84 into combustion apparatus 18 comprising an annular series of cylindrical combustion units 90 which deliver hot gases into a duct 92. The latter discharges the gases through a full-admission inlet nozzle to drive turbine wheels 98, 114, which drive the respective compressor sections, and to either drive a further turbine wheel having an output shaft 30 or exhaust through a nozzle to produce propulsive thrust. Alternatively, the two compressor sections may be driven by a single turbine wheel via gearing. Sump housings 54, 72, 120 for the shaft bearings are each sealed at both ends by friction or labyrinth seal assemblies 60, 74, 106, 122.

Refrigeration system having a screw compressor with an auxiliary high pressure suction inlet

Abstract: A refrigeration system having a screw compressor for compressing low pressure suction gas that is received from an evaporator and compressing it and discharging it into a condenser; including an auxiliary high-pressure suction inlet to the compressor for conducting high-pressure suction vapor from a pressure-reducing means and to the compressor for being compressed along with lowpressure suction vapor. The invention is used with a refrigeration system having either two operating suction pressure levels, or having a single suction level. The high-pressure suction vapor is introduced into the compressor at a point after the low-pressure suction is cut off, and therefore no reduction in the low-pressure suction capacity results. Increased compressor capacity is thus accomplished by the addition of this high pressure vapor.

Combination compressor casing-air manifold structure

Abstract: A gas turbine engine compressor casing structure is disclosed which provides a full annular bleed orifice for bleeding compressor stage air to a plenum chamber surrounding the aft stages of the compressor and thence to a full annular chamber adjacent the engine''s combustion section. The compressor casing is constructed with an aft section which has an expanded diameter and is connected with the adjacent section of the engine structure by means of a bolted flange. A separate inner compressor casing is provided to support the latter stage stator vanes and telescopes within the outer casing. A lip is provided the forward end of the inner casing so that when it is assembled with the primary compressor casing, the lip forms in cooperation with the adjacent inner wall of the forward section of the primary casing an annular bleed orifice in the compressor inner wall. The full annular chamber is defined by an outer wall, an inner wall, and an end wall, and is in communication with the space between the aft section of the primary compressor casing and the inner compressor casing.

Rotary displacement machines

Abstract: A rotary compressor, vacuum pump, or expansion engine. Two interengaging rotors rotate within bores in a casing structure. Each rotor has a hub and a tooth. Plates are located against the four inside end walls of the two casing bores. The four plates are angularly adjustable so as to vary both the capacity and the internal pressure ratio. The machine has zero (or near zero) clearance volume so that (when operating as a compressor) substantially all of the compressed gas is delivered to the discharge ports.