Gas turbine pump unit

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

 

The invention relates to ground-based gas turbine units for mechanical drive, including installations with a pumping unit for pumping oil.

Known gas turbine unit, which includes located in the engine compartment of a gas turbine engine with the input device and the gearbox (Vasvar. Design of gas turbine installations, Meters: machinery, 1970, p.88, RIS).

A disadvantage of the known design is the low reliability because of the difficulty of assembling the transmission, as well as visual and instrumental monitoring of gas turbine compressor side of its entrance, as well as increased weight and dimensions of the input device.

Closest to the claimed gas turbine is the unit containing the turbocharger, the drive shaft of the external load and the gear (patent RU No. 2098649).

A disadvantage of the known designs adopted for the prototype, is its low reliability due to the lack of input snails, which can lead to the ingress of foreign objects from the compartment in which is located the turbocharger on the engine inlet with consequent damage to turbocharger impeller machine.

The technical problem on which the invention is directed, is to increase reliability, reduce weight and size of the gas turbine unit with the em run input device with telescopic joints, and also due to easy access to the compressor inlet for visual and instrumental monitoring and installation of the transitional shaft installation.

The essence of the technical solutions is that in the turbine pump unit located in the container of a gas turbine engine, gearbox and transitional shaft between them, according to the invention, at the outlet of the reducer installed the pump, and between the gearbox and the engine are input device, and a part of the front end wall of the input device is placed on the gearbox, and the rear end wall of the input device is located on the gas turbine engine, while both parts are connected in the axial and radial directions sealed telescopic connection with the remaining part of input devices mounted in the container and the front end wall of the input device has an input inspection hatch and the bottom wall of the input device is planar and horizontal.

The implementation of modern gas turbine units in block-container design allows these units are not only mobile, but also significantly reduce installation time and improve the reliability of these installations with fixed their performance. Weight and dimensions of the blocks in this case should also be minimal for transportation n the rail without restrictions on weight and external dimensions, and reliability is enhanced by factory-assembled block-container.

Installation at the outlet of the gear pump allows the use of a gas turbine unit for pumping fluid, for example oil, which reduces the weight of the pumping unit.

Installation between the gearbox and turbine engine input device allows to increase the reliability of the gas turbine unit by eliminating contact with the engine inlet foreign objects and arrange for cleaning incoming air engine.

The placement of the front end wall of the input device on the gearbox, and part of the rear end wall of the input device for a gas turbine engine with their connection in the axial and radial directions sealed telescopic connection with the remaining part of input devices mounted in the container, eliminates leaks at the engine inlet of polluted air from the container, and also eliminates the appearance of additional stress when mounting the engine and gearbox, as well as by thermal deformations of the engine, gearbox and container. It also reduces the weight and axial dimensions of the input device and the gas turbine installation, easier Assembly and disassembly of the engine and gearbox.

Execution of the input observation hatch in the front endwall of the WMO the nogo device provides access for installation of the transitional shaft, and the bottom wall of the input device is planar and horizontal, provides the necessary convenience when mounting the shaft. Performing input inspection door side of the engine is impossible because of the increased size of the engine, and the side walls of the input device performing the hatch is impossible due to limitations on the size of the container.

Input inspection hatch at the same time provides a visual and instrumental inspection of the compressor from the side of its entrance, as well as monitoring the status of the elastic front and rear couplings located between the transitional shaft and the shaft of the gas turbine engine, as well as transition between the shaft and the shaft of the gearbox.

1 shows a longitudinal section of a gas turbine installation.

Figure 2 - element I of Fig 1 in a larger view.

Figure 3 - element II of Fig 1 in a larger view.

Nafig - type a in figure 1.

Gas turbine pumping unit 1 is installed in the container 2 of the gas turbine engine 3 and connected to the transitional shaft 4 of the gearbox 5, the output of which is the pump 6. Between the gas turbine engine 3 and the gearbox 5 is the input device 7, part 8 of the front end wall 9 which is placed on the gearbox 5. Part 10 of the rear end wall 11 of the input device 7 is installed on the gas turbine engine 3. Front and rear 10 part connected to the front 12 and rear 13 sealed telescopic connections with the rest of the 14 input device 7, which is rigidly fixed to the container 2. Front telescopic tight connection 12 comprises a radial telescopic connection 15 with the sealing ring 16 and the axial telescopic connection 17 with the sealing rings 18 and 19. Rear telescopic tight connection 13 consists of radial telescopic connection 20 with the sealing ring 21 and the axial telescopic connection 22 with the sealing ring 23. Inside the input device 7 is placed transitional shaft 4 connected to the front elastic coupling 24 with gear 5 and the rear elastic coupling 25 gas turbine engine 3. In the front end wall 9 of the input device 7 is airtight input inspection hatch 26 connecting the internal cavity 27 of the input device 7 with a cavity 28 of the compartment 29 and is designed to ease installation of the transitional shaft 4 connecting the gas turbine engine 3 with gear 5. In addition, from the internal cavity 27 of the input device is a visual and instrumental control flow of the compressor 30 of the gas turbine engine 3, and the front flexible coupling 24 and the rear elastic coupling 25. The bottom wall 31 of the input device 7 is planar and horizontal.

The device operates as follows.

During operation of the gas turbine unit 1 gas turbine engine is tel 3 and the gear 5 are moved in the axial and radial directions relative to the input device 7 due to different thermal strains, however, this does not lead to damage of the engine 3, the reduction gear 5 and the input device 7, as a sealed telescopic connections 12 and 13 allow the displacement of the engine and of the gearbox relative to the input device 7 without breaching the past, which increases the reliability of the gas turbine unit 1. When working on wash flowing part of the gas turbine engine and visual inspection and instrumental control of the compressor 30 of the engine 3, as well as flexible couplings 24 and 25 maintenance work is carried out from the internal cavity 27 of the input device 7, where the staff goes through the front access door 26, the lower flat horizontal wall 31 of the input device 7 in this case serves as a floor for staff.

Turbine pump unit is placed in the container of a gas turbine engine, gearbox and transitional shaft between them, characterized in that at the outlet of the reducer installed the pump, and between the gearbox and the engine are input device, and a part of the front end wall of the input device is placed on the gearbox, and the rear end wall of the input device is located on the gas turbine engine, while both parts are connected in the axial and radial directions sealed telescopic connection with the OST is usasa part of the input device, fixed in the container, and the front end wall of the input device has an input inspection hatch, and the bottom wall of the input device is planar and horizontal.



 

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