RU33981U1 - Gas turbine engine - Google Patents

Abstract

A gas turbine drive engine comprising a fifteen-speed axial compressor with an inlet guide apparatus and air bypass valves, a combustion chamber, a gas generator turbine and a power turbine, characterized in that the compressor inlet guide apparatus is capable of opening at 4 ° in basic operating modes by the blade angle, and the gas turbine is made in three stages.

Description

Gas turbine engine

The utility model relates to gas turbine construction, in particular, to devices of gas turbine drives for supercharger drive in gas pumping units.

A known gas turbine drive engine comprising a fifteen-speed axial compressor with an inlet guide apparatus and air bypass valves, a combustion chamber, a gas generator turbine and a power turbine (see Utility Model Certificate RU 10425 U1, F 02 C 1/00, 07/16/99). This drive gas turbine engine does not fully comply with modern economic and environmental requirements.

The objective the utility model is aimed at is expanding the arsenal of gas turbine driving engines used to drive the supercharger as part of gas pumping units by increasing its rated power while ensuring the following requirements: interchangeability of the gas turbine driving engine with existing serial engines; interchangeability of a gas blower; the engine efficiency level should correspond to the best examples in this power class for gas pumping units with a simple cycle (, 0 ... 34.7%), as well as the maximum use of units and parts of commercially available engines.

The problem is solved in that in a driving gas turbine engine containing a fifteen-stage axial compressor with an inlet guide apparatus and air bypass valves, a combustion chamber, a gas generator turbine and a power turbine, the compressor inlet guide apparatus is openable

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in the main operating modes, at the 4 th corner of the blade installation, and the gas generator turbine is made in three stages.

The essence of the utility model is illustrated by drawings, where in Fig.1 shows the compressor rotor; figure 2 - compressor stator; in Fig.3 the blade of the inlet guide vane.

The driving gas turbine engine comprises a compressor, a combustion chamber, a gas generator turbine and a power turbine.

The compressor serves to increase the pressure of the air entering the combustion chamber, is made of a fifteen-stage axial and consists of a rotor 1 and a stator 2. The compressor rotor 1 has a drum-disk design and is mounted for rotation on two rolling bearings. The front bearing is roller, allowing axial movement to compensate for changes in the dimensions of the rotor 1 and stator 2 under the influence of temperatures and deformation from axial forces. The fixing of the rotor 1 in the axial direction is carried out in the rear angular contact ball bearing. The connection of the front shaft 3 of the compressor with the drive shaft of the central drive and the rear shaft 4 of the compressor with the front shaft of the turbine is splined. The compressor stator 2 consists of compressor housing 5, guide vanes 6 and working rings 7. With the front flange, the compressor housing 5 is rigidly attached to the rear flange of the front support housing, and the front flange of the combustion chamber is attached to the rear flange of the housing 5. For normal operation of the compressor in off-design conditions, four bypass valves are mounted on the compressor crankcase 5, which provide air bypass from the corresponding compressor stages.

To ensure stable operation of the compressor during start-up and expansion of the range of engine operating modes, an input guide vane is intended. The simultaneous change in the installation angle of all the blades at the inlet to the compressor allows for optimal conditions

for the operation of the first stage of the compressor. The compressor input guide vane in the main operating modes is opened at 4 by the blade angle.

The position of the blades 8 of the input guide vane, depending on the operating mode of the engine, is controlled by the control unit of the engine regulation system. An input guide vane is attached at the compressor inlet at the rear of the front support housing and consists of guide vanes 8, an inner ring, a detachable outer ring, pivot arms and a drive ring with a gear sector. The rotary blades 8 have two pins. The lower pin 9 is installed in the sleeve 10 of the inner ring, and the upper pin 11 is hollow, installed in the sleeve of the outer ring. A channel 12 for heating the blades with hot air is made along the body of the entire blade 8 along the inlet edge to prevent their icing. The channel opening 12 is connected to the upper pin 11. At the end of the channel 12 two oval outlet openings 13 are made 13. On the lower axles 9 of the blades 8, the pivoting levers are mounted and connected to them. The shoulder on the blades 8 and the end plane of the pivot arm prevent the blade 8 from falling out and fix it from radial movement. The inner ring is used to install the blades 8, accommodate the rotary mechanism and fasten the input guide vane to the front support. A drive ring is mounted in the inner ring with a bayonet-type shutter. The bayonet type of shutter provides the necessary angular rotation of the drive ring. A gear sector is mounted on the drive ring, which engages with the drive gear 14 and is used for angular rotation of the drive ring. The drive ring has radial grooves in which barrel-shaped heads of pivoting levers are located. The outer ring holds the blades in the radial direction. The input guide vane is centered in the front support.

The rotation of the blades of the input guide vane is as follows. The drive gear 14, which engages with the gear sector installed in the front support of the input guide vane, rotates together with the drive ring in an angular rotation. The barrel-shaped heads of the pivoting levers located in the grooves of the driving ring, following it, provide simultaneous rotation of all the guide vanes 8, Operational restriction of rotation of the vanes is provided in the hydraulic booster of the input guide vanes. In the event of a hydraulic booster failure, an “emergency stop of the gear sector in the cheeks of a special limiter mounted on the front support occurs.

The gas generator turbine is designed to drive the compressor rotor, as well as the units serving the engine, in order to increase the efficiency, a three-stage axial is made and consists of a turbine rotor and a stator. The turbine rotor consists of three impellers, centered between themselves and pulled together by pins. The rotor rotates on two roller bearings. The front bearing is installed in the bearing housing of the turbine housing, and the rear - in the intermediate support of the turbine. Axial forces are perceived by the ball bearing of the compressor rotor. The working blades of the 1st and 2nd stages are cooled by air. The turbine stator consists of a nozzle device of the first stage with cooled blades and nozzle devices of the second and third stages. Outer and inner rings with inserted blades form channels for gas entering the rotor blades. In order to limit gas leakage between the turbine stages, gas labyrinth seals are installed.

The driving gas turbine engine operates as follows.

enters the compressor, where it is compressed and enters the combustion chamber, in which it is mixed with fuel gas entering there. The combustible, air-fuel mixture enters the gas generator turbine inlet, passing through which it expends its energy to rotate the gas generator rotor, enters the free turbine, where, expanding, it rotates the rotor of the free turbine, which, in turn, spins the supercharger. The content of nitrogen oxides NOx in the exhaust gases of the engine does not exceed 50 mg / nm (in a dried sample at 0 ° C, 0.1013 MPa and a nominal volumetric oxygen concentration of 15%). The content of carbon monoxide CO in the exhaust gases of the engine does not exceed 100 mg / nm (in a dried sample at 0 ° C, 0.1013 MPa and a nominal volumetric oxygen concentration of 15%).

Thus, the proposed utility model allows to expand the arsenal of gas turbine engines used to drive the supercharger as a part of gas pumping units due to the design of the utility model, which determines the increased power and efficiency, improved environmental characteristics of the engine while increasing its resource.

Claims (1)

A gas turbine drive engine comprising a fifteen-speed axial compressor with an inlet guide apparatus and air bypass valves, a combustion chamber, a gas generator turbine and a power turbine, characterized in that the compressor inlet guide apparatus is capable of opening at 4 ° in basic operating modes by the blade angle, and the gas turbine is made in three stages.