RU2807828C1 - Gas turbine engine with two injector blocks - Google Patents

Abstract

FIELD: gas turbine engine.

SUBSTANCE: gas turbine engine with two blocks of nozzles includes a cylindrical body with inlet and outlet windows, in the cavity of which a turbine wheel is installed, along the circumference of which there are radial blades. There are skirts on the sides of the wheel, which are in contact with the removable turbine walls. Between the removable turbine walls and the removable walls of the housing, two cavities are formed in which compressor discs with blades located around the circumference of the disks are installed. The compressor disc bushings and the turbine wheel bushing are rigidly fixed to the turbine shaft. The compressor cavities communicate through radial holes with longitudinal windows made in the circumferential walls of the housing and in the removable walls of the housing. The blocks with injectors are placed outside the engine housing and connected to the engine body by means of guide pipes, the ends of which are equipped with flanges, one end is rigidly attached to the base of the injector block, and the other end is rigidly attached with flanges to the engine body. The guide pipes of both blocks are installed at an angle of 90 degrees to the plane of the turbine blades. The closed combustion chambers in each block with nozzles include the cavities of the blocks, the cavities of the guide pipes and the cavities between the turbine wheel blades. The intake pipe is attached to the engine body from the outside by means of flanges made along the pipe, and to the side wall of the injector block by flanges made on the transition cavity.

EFFECT: simplifying the design, reducing the size, increasing reliability, increasing power and obtaining a closed combustion chamber.

3 cl, 21 dwg

Description

The invention relates to gas turbine engines, the operating principle of which is based on the interaction of expanding gases in a closed combustion chamber with the blades of a working turbine,

Well-known gas turbine engines using a closed combustion chamber include a gas turbine engine with coupled turbines, registered in the State Register of Inventions (see Patent No. 2172855, issued to me on August 27, 2001).

This gas turbine engine contains a split housing, two coupled turbines mounted on parallel shafts. Each of the turbines is made in the form of a set of flat-walled disks rigidly mounted on shafts; radial depressions are made around the circumference of the disks. The turbine disks mutually enter the spaces between each other's disks and mate with their circumferential surfaces with the circumferential surfaces of the bushings. Each turbine is equipped with removable valves installed between the exhaust port and the combustion chamber. The valves are made detachable from packages of plates with gaps between them, and are attached to the body on common bases. The valve profiles are made with the opposite configuration to the profiles of the disks and spaces at the turbines and fit freely between the disks. The inner circumferential surfaces of both valves mate with the circumferential surfaces between the disk bushings. The circumferential surfaces of the bushings mate with the circumferential surfaces of the spaces between the plates. As a result of this, a closed combustion chamber is formed between the turbine interface line and the walls of the two fixed valves.

The disadvantage of this gas turbine engine is its design feature, which includes two interconnected turbines and two shutters, through which a known closed combustion chamber is created and achieved. As a result, this device leads to excess size, complexity and lack of efficiency.

The purpose of the present invention is to simplify the design, reduce the size, increase reliability, increase power and obtain a closed combustion chamber.

In the proposed gas turbine engine, the process of expansion of working gases occurs in two closed combustion chambers located inside two blocks with nozzles installed outside the housing on opposite sides. Working gas from two closed chambers is supplied directly to the turbine blades at an angle of 90 degrees. The exhaust gas is carried out through the cavities between the blades to the exhaust windows. After exhaust gases are released, these cavities are filled with air pumped by compressors and transferred to the area of closed combustion chambers of fuel products. Each injector block contains one spark plug and four injectors, two of them work with fuel, and two with gas (conditional option).

In order to create complete combustion of fuel products, one nozzle can be used to supply air. The nozzle blocks and outlet windows are located on the body relative to each other in the diametrical plane,

In order to cool the nozzle blocks and the turbine housing, windows are provided through which forced air flow is carried out created by two compressors

Fig. 1. Gas turbine engine with two blocks of nozzles, general view.

Fig. 2. Gas turbine engine with two injector blocks, front view.

1. Housing of a gas turbine engine with two nozzles. 2-3. Exhaust windows 4. Motor shaft. 5 Connecting flange. 6. Pipe for air intake. 7. Body of the injector block (two pieces). 8-9. Injector sockets. 10. Through holes for air intake. 11. Overhead edges of pipe fastening (flanges). 12. Guide pipe for high pressure working gases. 13. Flanges for fastening the guide pipe. 14. Windows for air intake. (The sides of the injectors are made identically).

Fig. 3. Gas turbine engine with two injector blocks, rear view.

1. Gas turbine engine housing. 2-3. Exhaust windows. 4. Motor shaft. 5. Connecting flange. 6. Pipe for air intake. 7. Cone of the injector block (two pieces). 8-9. Injector sockets. 10. Through holes for air intake. 11. Overhead edges of pipe fastening (flanges). 12. Guide pipe for high pressure working gases. 13. Flanges for fastening the guide pipe. 14. Windows for air intake

Fig. 4. Gas turbine engine with two blocks of nozzles, the section is given along the plane of the turbine wheel and the engine housing block.

1. Gas turbine engine housing. 2-3. Exhaust gas outlet windows. 4. Turbine wheel shaft. 5. Turbine hub. 6. Pipe for air intake, 7. Block of nozzles (two pieces). 8-9. Injector sockets. 10. Through hole for air intake. 11. Overhead flanges for attaching the pipe. 12. Guide pipe for working gases. 13. Flanges for attaching the guide pipe to the body. 14. Ventilation windows. 15. Oblique cutout for the start of exhaust gases escaping. 16. Guide nozzle for the exit of working gases. 17. Turbine wheel. 18. Turbine wheel blades. 19. Turbine skirt. 20. Blowing windows (four pieces for each pipe) additionally ensure air intake through the cavity of pipe-6. 21. The arrow shows the direction of pressure of the working gases.

Fig. 5. Housing of a gas turbine engine, a section showing the plane of the turbine shaft.

1. Motor housing. 4. Turbine shaft. 5. Turbine hub, 17. Turbine wheel (disk), 18. Turbine blades. 19. Turbine skirt. 20. Purge windows for cooling the engine housing and blocks with nozzles, 22-23. Side walls of the engine housing. 24. Turbine shaft bearings. 25-26. Turbine wheel walls.. 27-28. Compressor wheel disks. 29-30. Compressor wheel hubs. 31-32, Compressor disc blades. 33-34. Cavities for compressors. 35. Window for air intake by the right compressor. 36. Window for air intake by the left compressor. 37-38. The arrows show the window for the entry of air from the compressor into the cavity between the turbine blades. 39 The arrows show a window for the release of excess gas pressure that has broken through the gaps between the walls of the turbine skirt. 40-41. The places where the turbine walls are rigidly attached to the inner walls of the engine housing are shown. 42. Internal cavity of the turbine.

Fig. 6-7. Turbine wheel, side view and section shown along A-A in Fig. 6.

5. Hub. 17. Disc. 18. Shoulders. 19. Skirt. 42. Cavity.

Fig. 8-9. The cylindrical engine housing, the side walls are removed and a section along A=A is shown in Fig. 8.

1. Gas turbine engine housing. 2-3. Exhaust windows. 15. Oblique cutout for exhaust gas outlet. 16. Window for the exit of working gases. 20 Ventilation windows. 35-36. Communicating radial holes (or windows) with cavities 33 and 34 of the compressors.

Fig. 10-11. Front wall of the turbine. (The back and front walls are identical) and the section along A-A in Fig. 10

25. Turbine wheel wall (two pieces). 33. Compressor cavity. 35. Window for air intake by the right compressor. 39. A hole for the release of leaked gases into the gaps between the walls of the turbine wheel and the walls of the turbine. 40. Places where the walls are attached to the engine housing.

Fig. 12-13. The front wall of the engine housing is shown in section along A-A in Fig. 12.

22. Front side wall of the engine housing. 24. Bearing seat. 43. Intake windows (or 8 holes) are used to cool the engine housing, through which the air is sucked in by the rear air compressor.

Fig. 14-15. The rear wall of the engine housing and the section along A-A in Fig. 14

23 Rear side wall of the engine housing. 24. Bearing seat. 44. Intake windows (8 holes) used to cool the Engine housing, through which the air is sucked in by the front air compressor.

Fig. 16-17. Compressor wheel, front view and section along A-A in Fig. 16.

27. Compressor wheel disk. 30. Compressor wheel disc hub. 32. Shoulder blades.

Fig. 18-19. The upper nozzle block is shown in front view and a longitudinal section of the intake pipe 6 is shown.

1. Motor housing. 3. Exhaust gas outlet window. 7. Injector block housing 11. Overlay flange for attaching pipe - 6 to the engine housing. 8, 46. Injector sockets, top view. 9. Sockets for injectors (three pieces), located on the left side of the block. 45. Spark plug socket. 10, 48 Through channels (passage along the arrows, 52 - entrance).

47. The dotted line shows the working cavity, which communicates with the guide pipe 12. 49. Four radial windows that communicate with the longitudinal windows 20 of the housing. 50. A section of the intake pipe is shown - 6, 55. Pipe cavity. 54. Transitional cavity of the pipe.

Fig. 20. Diagram of the control mechanism for the operation of injectors, 56, 57, 58, 59. Four injectors and two spark plugs include one injector block. 60, 61, 62, 63 Includes four switches. 64, 65, 66, 67. Includes four pumps. 68, 69, 70, 71. Includes four rollers with cams. 72. Pipes return unused fuel back to Tank .73. The arrows show the direction of fuel in the pipelines. 74. The arrows show the directions of fuel in the pipelines, which has leaked into the gaps of the plungers at the injectors. 75-76. Four cams on a common shaft are located 90 degrees relative to each other.

Fig. 21. Scheme of engine starting and shielding from radio interference.

77. Ignition key. 78. Battery. 79. Starter. 80. Dynamo. 81 Induction coil. 82. Distributor. 83. Spark plugs. 84. Noise suppressing capacitors. 85 Shielded coupling. 86. Shielded tip. 87. Loudspeaker. 88.Radio receiver. 89. Antenna wire. 90. Whip antenna.

The design of a gas turbine engine with two blocks of nozzles.

A gas turbine engine with two blocks of nozzles includes a housing 1 (see Figs 2, 3 and 4), made of a cylindrical shape with two exhaust windows 2 and 3 located on the sides in the same diametrical plane. A turbine wheel with a shaft is installed in the cylindrical cavity of the housing 4 and hub 5 (see Fig. 5, 6, 7). Along the circumference of the wheel rim there are blades 18 located in the radial plane. Integral with the rim are skirts 19, disk 17 and hub 5 on both sides. Two turbine walls 25, 26 are installed on both sides of the turbine wheel with the shaft (Figs. 5 and 10, the walls are identical). The walls are equipped with a rim 40 and 41 (Fig. 5) made from one side of the walls, loosely mounted on the shaft and rigidly fixed with their rims 40 and 41 to the inner walls of the housing (see Fig. 5). The walls have windows 39 designed to communicate the cavity of the turbine wheel with the cavities of the compressor pumps 33, 34. The windows are made to cool the cavity of the turbine wheel and to remove leaked gases into the gaps between the walls of the skirts and walls of the turbine wheel. Windows 37, 38, made on the walls of the turbine, are designed to supply air from the compressors into the cavity between the turbine blades (see shown by arrows). On the circumferential walls of the rim and the walls of the housing there are radial holes 35, 36 (Fig. 5), through which constant communication is ensured between the longitudinal holes 20 made in the walls of the housing and the compressor cavities 33, 34. The hubs 29 and 30 of the compressor disks 27, 28 and the turbine hub 5 is rigidly fixed to the shaft 4. The compressor disks are equipped with blades 31, 32 located along the circumference of the disks and at an angle of 45 degrees to the walls of the disks (Fig. 16, 17). The turbine shaft is mounted on bearings 24, fixed in sockets made in the side walls of the housing 22 and 23 (Fig. 5 and 12, 14).

The front and back walls of the case are different from each other. At the front wall (Fig. 12), intake windows (or holes) 43 (eight pieces) are made in the lower part of the wall on the right side. The intake windows are designed to cool the engine housing; through them, the air is sucked in by the rear air compressor through blades 31 (Fig. 5) through radial holes 35 into the cavity 35 of the compressor. The air intake is carried out through longitudinal windows 20 and intake windows 43 (Fig. 12).

At the rear wall (Fig. 14), intake windows 44 (eight pieces) are made in the upper part on the right side. The intake windows are designed to cool the housing, through them the air is sucked in by the front air compressor through blades 32 (Figs. 5 and 16), through radial holes 36 into the cavity 34 of the compressor. The air intake is carried out through longitudinal windows 20 (Fig. 5) and intake windows 44 (Fig. 14).

The gas turbine engine is equipped with two blocks 7 (Fig. 4. 18, 19) with nozzles. The blocks are located on opposite sides of the body. Each block contains a guide pipe 12 and a pipe 6 for air intake. One end of the guide pipe is rigidly attached by means of a flange to the bottom of the injector block housing, and the other end is rigidly attached by means of a flange 13 to the surface of the engine housing. The guide pipe 12 is designed to direct the explosive effect of fuel products during combustion onto the turbine blades. A closed combustion chamber is formed between the internal cavity of the injector block, the cavity of the guide pipe and the cavities between the turbine blades.

To create the greatest efficiency effect, during the explosion of fuel products, the guide pipe 12 and window 16 (Fig. 4 and 18) are made at an angle of 90 degrees to the plane of the turbine blades (see the arrow in the cavity of window 21, it shows the direction of action of the working gases from block cavities).

To cool the nozzle block, intake pipe 6 is used (see Figs. 18, 19). Air is sucked in along the arrows 52, passes through longitudinal windows 10, 48 made on both sides of the block, passes through the transition cavity 54 and enters the longitudinal cavity 55 of the intake pipe. The longitudinal cavity 55 communicates through radial holes 49 (four pieces) with longitudinal windows 20 (Fig. 18) made in the walls of the engine housing. The cavity of the closed combustion chamber 47 (see shown by the dotted line 47) is separated from the through cavities 10, 48 by walls 53. The air, passing the longitudinal windows 20, is sucked through the radial windows 36 (Fig. 5) by the blades 32 of the left compressor. In the cavities 33 and 34 of both compressors, air pressure is created, which is supplied through windows 37 and 38 (arrows) in the cavity between the turbine blades 18. The turbine cavities transfer air to the combustion zone of fuel products of closed chambers 16, 21 of both blocks (Fig. 4), and an explosion of the products occurs. As soon as the turbine cavities reach the cutouts 15, the exhaust gases will be released through the exhaust windows 2 and 3.

Diagram of the injector operation control mechanism

In fig. Figure 20 shows a diagram of the interaction of the injectors with the control mechanism. One injector block includes four injectors 56, 57, 58, 59, four switches 60, 61, 62, 63, four pumps 64, 65, 66, 67 with cam drive 68, 69, 70, 71. The cam mechanism works with plunger pumps in sequential order. With one revolution of the camshaft, compression occurs in each pump. Cam 75 is shown in its operating position, and cam 76 is rotated 270 degrees relative to the first cam. Therefore, each cam is rotated 90 degrees relative to each other.

All injectors of both blocks are connected to one cam drive. The drive can be performed independently of the rotation of the turbine shaft and have more different rotation speeds.

Pump 64 shows the compression of the working mixture (symbolic cross). The remaining three pistons do not work, waiting for the cam to turn. When the fuel is compressed by the piston, the fuel enters the lower fitting of the switch 60 and exits through the upper fitting and through pipeline 73 enters the injector injector 56. The injector is activated and injection occurs. During the operating position, all switches are in the open position. The injectors are disconnected from the fuel supply by turning the knob to the “down” position (arrow). The fuel that seeps through the gaps between the walls of the plunger exits through the upper fitting and is discharged through pipeline 74 back to the pump inlet or into the fuel tank.

Switches, injectors and pumps are all made according to the same design. The switches are designed to turn on or turn off the injectors from operation. For example, if you need to reduce the power of the engine, you can turn off several injectors on one of the blocks; to do this, the switch levers must be turned downward. At the same time, the left cavity will open and the right cavity of the switches will close, the injectors will turn off, and the fuel from the pumps will exit into the left fitting of the switches and flow back into the fuel tank. The cam shaft can be used for eight injectors; for this, rollers with pistons can be connected on both sides of each cam.

Starting an engine with two injector banks.

In fig. Figure 21 shows the ignition diagram (old diagram, taken from a textbook on cars). To start the engine, the ignition key 77 is turned on. The starter 79 is activated from the power supply 78 and the turbine begins to rotate, at the same time the induction coil 81 and the distributor 82 are turned on. An ignition spark is generated, which is supplied to the spark plugs 83, which are installed in blocks with injectors. When fuel is injected by injectors, the fuel ignites in both blocks, gas pressure arises in closed chambers, which will act on the turbine blades and cause it to rotate. After which you can use switches, fig. 20, set the required engine power, i.e. it becomes possible to change the turbine rotation speed within wide limits. This is necessary and important for aircraft. As soon as the turbine with the shaft begins to rotate, the dynamo 80 is automatically connected, which is designed to generate electrical energy to charge the battery.

Energy is also used to operate the radio 88 and radio communications.

Claims (3)

1. A gas turbine engine with two blocks of nozzles, including a closed combustion chamber of fuel products formed in the cavity between two mating turbines mounted on parallel shafts, and two gates attached to the inner walls of the split housing, a set of disks of the left and right gates is made in reverse configuration relative to the set of turbine disks and freely fits into the spaces between the disks, characterized in that in order to simplify the design, reduce dimensions, increase reliability, increase power and obtain closed combustion chambers using various fuel products, the expansion process of working gases occurs in a gas turbine engine in two closed combustion chambers located inside two blocks with several nozzles installed on the surface, on opposite sides of the turbine body, the working gas from the closed combustion chambers is supplied through guide pipes directly to the turbine wheel blades at an angle of 90 degrees, the exhaust gas is carried out by the cavities between the blades to the exhaust windows, after exhaust gases are released, these cavities are filled with air, pumped by two compressors, and then transferred to the area of closed combustion chambers of fuel products, each injector block contains one spark plug and four injectors, two injectors operate on gas, the third operates on liquid fuel, the fourth - supplies air; in order to cool the nozzle blocks and the turbine housing, purge windows are provided through which air is blown from two compressors. 2. The gas turbine engine according to claim 1, characterized in that in order to increase the efficiency of the working gas, the radial blades of the turbine wheel are located along the circumference of the turbine wheel rim. 3. Gas turbine engine according to claim 1, characterized in that in order to disconnect the injectors from the operating state, each injector is equipped with a fuel product supply switch.

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