Gas-turbine unit

FIELD: power engineering.

SUBSTANCE: proposed gas-turbine unit has low-pressure compressor, intermediate air cooler, high-pressure compressor, regenerator, combustion chamber, gas turbine wherefrom spent gas is conveyed to regenerator coupled with exhaust pipe that uses energy of exhaust gases and is provided with nozzle and intake chamber for cooling down atmospheric air arriving from intermediate air cooler. Proportion of exhaust pipe parts is chosen to ensure desired proportion of sizes of gas-turbine components.

EFFECT: enhanced reliability of gas-turbine unit and ability of its off-line operation.

1 cl, 1 dwg

 

The invention relates to power engineering, in particular to azotobacteria.

Known gas turbine, consisting of a low-pressure compressor, an intermediate cooler, high pressure compressor, regenerator, combustion chamber, gas turbine and the exhaust pipe.

(See the book AGS “Thermal tests of stationary gas turbines. Meters, Energy, 1971, str).

Known the same design gas turbine installation (See. the article “Intercooled and Recuperated Dresser-Rand DC990 Gas Turbine Engine - p.2, presented at the international Congress in 1989, Toronto, Ontario, Canada - prototype).

The disadvantage mentioned gas turbine plants is that as a refrigerant for the intermediate coolers used liquid, mainly water. And this requires additional capital and operating costs of water treatment, the organization of water circulation and cooling in cooling towers or other devices, feeding circulation circuit through evaporation and entrainment of water in its cooling atmospheric air. The salt deposits and surface contamination of the air cooler on the water side leads to a significant reduction of the parameters of the gas turbine installation. In addition, the effect of the intermediate cooling in winter underutilized, because the contour of the circulating water temperature is maintained, guaranteeing the absence of freezing.

Known use as a refrigerant directly to the atmospheric air (See. directory “Standardized air cooling units General purpose” CONTAINERTYPES, M., 1973).

Obstacle for the application of air cooled in the intermediate cooler gas turbines are large size and high power fan cooling air feeding, as its consumption is several times higher than the consumption cycle air (Cm. the article “Intercooled and Recuperaed Dresser-Rand DC990 Gas Turbine Engine "), presented at the international Congress in 1989, Toronto, Ontario, Canada, p.4. In addition, failure of the fan or the power supply is an emergency stop of the gas turbine installation because of error compressor high and low pressure.

Object of the present invention is to improve the reliability of gas turbines and ensuring its independence.

This object is achieved in that in the gas turbine installation as a refrigerant used by the air, and proso cooling air is exhaust pipe with nozzle and a receiving cell.

The essential features of the invention are the low-pressure compressor, intercooler, comp is essor high pressure, the regenerator, combustor, gas turbine, the exhaust pipe with nozzle and intake chamber.

The hallmark is that the exhaust pipe is made with nozzle and performs the function of a jet pump that uses the energy of the exhaust gases to procosa cooling air through the intermediate cooler with a receiving cell.

The drawing schematically shows a gas turbine power plant, consisting of a low-pressure compressor 1, the intermediate air cooler 2, the high-pressure compressor 3, the regenerator 4, the combustion chamber 5, the gas turbine 6, the exhaust pipe 7 with the nozzle 8 and the reception chamber 9 for cooling air.

Setup works as follows:

Cyclic air is sucked and compressed in the low-pressure compressor 1, is directed into the intermediate air cooler 2, is cooled by atmospheric air and enters the high-pressure compressor 3, there is compressed and enters the regenerator 4, where it is heated, and then flows into the combustion chamber 5, the combustion products produced work in the gas turbine 6. Exhaust gases are routed to the regenerator 4, then into the exhaust pipe 7, which are accelerated in the nozzle 8, creating a vacuum in the receiving chamber 9, under which the cooling air promazyvaetsya through the intermediate cooler 2. Narrative intermediate cooler 2 for cooling air mixes with the exhaust gases in the exhaust pipe 7 and dumped them into the atmosphere.

The cost of the cooling air and combustion products for completed construction of the exhaust pipe is determined by the given factor ejection (5)

where Ginand Tin- mass flow rate and the absolute temperature of the cooling air entering the receiving chamber 9, a Ggand Tg- mass flow rate and the absolute temperature of the exhaust gases for the regenerator. The value of UCRremains constant as partial load, and the change of parameters of atmospheric air. In the proposed scheme provides autonomy and assured flow of cooling air into the intermediate cooler 2 while the gas turbine installation in the work and the exhaust gases pass into the exhaust pipe.

Gas turbine installation comprising a low-pressure compressor, an intermediate cooler, high pressure air compressor, regenerator, a combustor, a gas turbine, the exhaust gas from which is directed to a regenerator associated with the exhaust pipe, using the energy of the exhaust gases and with a nozzle and a suction chamber for the cooling of atmospheric air coming from the intermediate cooler, characterized in that the coordination of the parts of the exhaust pipe is selected which provides the ratio is s

where GIn- mass flow rate of cooling air flowing from the intermediate cooler at the entrance to the receiving chamber;

TInis the absolute temperature of the cooling air flowing from the intermediate cooler at the entrance to the receiving chamber;

Gg- mass flow rate of exhaust gases with the regenerator;

TGis the absolute temperature of the exhaust gases for the regenerator.



 

Same patents:

The invention relates to the field of aircraft propulsion, specifically to aircraft engines with built-in generators, resulting in rotation without an intermediate gearbox

The invention relates to the field of energy and can be used in heat exchange systems for gas turbine units (GTU) with a liquid or gaseous coolant

Gas turbine engine // 2168024
The invention relates to the field of power engineering, mainly for small aircraft engines

The invention relates to the field of aircraft engine industry, and transport machinery, in particular the invention relates to the placement and mounting of auxiliary devices when the aircraft gas turbine engine is not placed on the dimensions of the engine compartment of the plane or when you want to place the engine more power in the dimensions of the engine compartment of an existing aircraft

Gas-turbine unit // 2245448

FIELD: power engineering.

SUBSTANCE: proposed gas-turbine unit has low-pressure compressor, intermediate air cooler, high-pressure compressor, regenerator, combustion chamber, gas turbine wherefrom spent gas is conveyed to regenerator coupled with exhaust pipe that uses energy of exhaust gases and is provided with nozzle and intake chamber for cooling down atmospheric air arriving from intermediate air cooler. Proportion of exhaust pipe parts is chosen to ensure desired proportion of sizes of gas-turbine components.

EFFECT: enhanced reliability of gas-turbine unit and ability of its off-line operation.

1 cl, 1 dwg

FIELD: aircraft engineering; gas turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device to transmit torque from compressor shaft to box of auxiliaries of gas-turbine engine includes spur gear wheel and bevel gear spaced and connected by seat surfaces and splines. Bevel gear is mounted on separate bearing support. Inductor is fitted in inner space of spur gear.

EFFECT: improved reliability of engine by provision of accurate signal from device checking frequency of rotation of compressor rotor.

1 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device contains fastening members and movable member telescopically connected with casing. Movable member is on accessory gear box and secured by pressure flange for displacement along end face of box. Clearance is formed between mating surfaces of flange and movable member.

EFFECT: improved reliability of connection of casing and accessory gear box by providing their rigid connection and sealing of inner spaces.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to aviation and particularly to devices for restraint and arrangement of auxiliary equipment in turbojet engines. The device consists of two coaxial rings (12, 14) assembled one into another and connected to each other with hollow radial poles (16, 18, 20 and 22). The pipelines and electrical wires run inside poles. At least one of the side poles (16, 18) bears a removable panel (24, 26) on its side, which after dismounting facilitates an access to the equipment of the turbojet engine arranged radially inside the interior ring (12) in one line with the radial pole (16, 18). Such design of the device provides an access to the equipment, installed in a turbojet engine.

EFFECT: facilitating access to equipment, assembled in a turbojet engine due to arrangement of a restraining device and of auxiliary equipment.

10 cl, 5 dwg

FIELD: electricity.

SUBSTANCE: cable bundle (3) positioning and retaining station on the turbojet engine (1) housing (2) includes bundle supports (3) standardized for directions perpendicular to the turbojet engine (1) axis (4) and bundle supports standardised for directions parallel to the turbojet engine (1) axis (4).

EFFECT: reduction of manufacturing cycle cost and time.

14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: invention is intended for feeding electric power to equipment from gas turbine engine. The proposed system comprises an electronic control device to control, at least, one parameter containing the data on originating variation in consumed power, a control valve controlled by aforesaid system and feeding air take off the engine operated in transient conditions and a pneumatic device receiving aforesaid taken-off air to actuate the aircraft onboard equipment. The latter can represent an air turbine or generator with built-in pneumatic circuitry.

EFFECT: use of engine pneumatic power to drive aircraft onboard equipment.

33 cl, 10 dwg

Air engine design // 2355902

FIELD: engine engineering, aviation.

SUBSTANCE: in accordance with the present invention fillet fairing is installed inside bypass channel of the external engine circuit in order to avoid outer thickness of auxiliary mechanisms and gear boxes and to actuate them. The external circuit channel is between engine housing and inner circuit of compressor/engine turbine. The fillet fairing dimensions are enough to accommodate auxiliary mechanisms. At the same time the external circuit channel is correspondingly made axisymmentrical to avoid or compensate any blocking effect from fillet fairing within the channel limits when air flows. In addition the fillet fairing may be provided for placing engine oil tank as well as filter/heat exchanger mechanisms foreseen for engine. Under the above circumstances it is essential that elongated cylindrical engine profile is maintained so that reduced cross section is required allowing for the engine to keep a reduced glider of air craft. As a result acoustic shock waves profile is improved.

EFFECT: elimination of outer thickness when auxiliary mechanisms are placed.

FIELD: engines and pumps.

SUBSTANCE: proposed unit consists of gas turbine and reduction gear accommodated inside container and coupled via transfer shaft, reduction gear output shaft carrying the pump. Input device is arranged between said reduction gear and engine so that device front face wall part seats on reduction gear, while device read face wall part is located on gas turbine engine. Note here that both aforesaid parts are linked up axially and radially by sealed telescopic couplings with the remaining part of input device fixed container. Inlet inspection window is made in input device front face wall. Input device lower wall is made flat and horizontal. In operation, sealed telescopic couplings allow the engine and reduction gear to move relative to input device with no loss in tightness on the latter.

EFFECT: higher reliability, reduced weight and overall dimensions, easier mounting and control.

3 dwg

FIELD: machine building.

SUBSTANCE: unit consists of gear box of gas turbine and of at least one starter/generator mechanically coupled with gear box. The gear box consists of gears with several pinions. The starter/generator contains a generating block with a rotor, forming an inductance coil and stator forming an anchor; further, the stator/generator contains an actuating block with the stator forming the inductance coil and rotor forming an anchor connected to the inductance coil of the generating block. The rotor of the generating block and the rotor of the actuating block are arranged on a common shaft with a pinion engaging the gear of the gear box on both sides of this pinion. The invention facilitates integration of the starter/generator into the gear box of the gas turbine.

EFFECT: reduced volume and dimensions, ensuring easy disassembly.

23 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: auxiliary mechanism drive of two-shaft gas turbine engine comprising high- and low-pressure shafts incorporates first mechanical transmission between high-pressure shaft and drive box, and hydraulic transmission between low-pressure shaft and drive box. Auxiliary mechanisms are arranged in drive box, while hydraulic transmission is mounted to allow auxiliary mechanism drive rpm being equal to high-pressure shaft rpm.

EFFECT: possibility to take off power from high- and low-pressure shafts without varying auxiliary mechanism rpm.

14 cl, 3 dwg

Up!