RU2463464C1 - Gas turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises housing to accommodate rotor with combustion chambers and turbine. Housing has cover. Rotor is rigidly coupled with engine shaft. Turbine rests on shaft to run thereon and is fitted in turbine housing. Rotor is fitted in rotor case. Rotor case and turbine housing are rigidly jointed together. Combustion chambers are arranged all around the rotor, each having a fuel feed hole on one rotor side and nozzle made on the opposite side. Space disc with openings is arranged between rotor and turbine and rigidly jointed with rotor case and turbine housing. Every said opening makes channel to communicate rotor combustion chamber with turbine working space. Turbine incorporates drum arranged around the shaft and furnished with hollow support rigidly coupled therewith to run in bearings on engine shaft and there around. Engine housing cover has section elongated along the shaft to house reduction gear. Reduction gear shaft is engaged with aforesaid drum via ring gear arranged on drum cover end part. Reduction gear output idle shaft has means to engage it with oil pump and compressor.

EFFECT: higher reliability.

3 cl, 32 dwg

Description

The technical solution presented in this description relates to internal combustion engines, in particular to rotary engines whose rotors have constant-volume combustion chambers, while such engines are functionally and constructively coupled to gas turbines, as well as to compressors, the working cavities of which, as a rule, through mixers of the working mixture communicated with the working chambers of the rotor.

Gas turbine units are known, each of which contains a housing with combustion chambers, a turbine and a compressor, the latter being connected through the mixer to the combustion chambers that are connected to the turbine cavity in which its blades are located, and the compressor shaft is connected to the turbine shaft (" Gas turbine units with combustion at a constant volume ", G.V. Zhiritsky," Installations with combustion at a constant volume "," State Energy Publishing House. M.-L., 1948, p. 37 .; Ya. I. Schnee, " Gas turbines. ”M.:“ Mashgiz ”, 1960, p.11).

Gas turbine engines are also known, each of which contains a housing, in the housing there is a rotor with working chambers located around the circumference of the rotor, on the one hand each chamber has an opening for introducing the working mixture into it, on the other hand the chamber has a nozzle located at an angle to the axis chambers, the rotor is mounted on a shaft on which a turbine with blades is fixed at its periphery (RU 2147341 C1, publ. 2000.04.10; RU 2096639 C1, 1997.11.20; RU 2282734 C2, 2006.08.27 and RU 2263805 C2, 2005.11.10 )

Similar technical solutions are presented in the descriptions of gas turbine engines GB 569534, US 3899874 and GB 2216956, in each of which a rotor with working chambers located around the circumference of the rotor is located in the housing, on the one hand each chamber has an opening for introducing the working mixture into it, on the other the side of the chamber has an outlet, and the rotor is mounted on a shaft on which a turbine with blades is mounted.

In known gas turbine engines, a significant part of the power is spent on mechanical losses that are associated with the conversion of gas energy into torque on the engine shaft, while the energy conversion means available in the known solutions significantly complicate the design of the engines.

A close technical solution to this invention is a gas turbine engine containing a rotor located in the housing with combustion chambers and a turbine that are mounted on the same shaft, the combustion chambers are located around the circumference of the rotor and each of them has an opening for supplying the working mixture to it, and on the other side there is a nozzle, in the case between the rotor and the turbine there is a distribution disk connected to the case with windows, each of which forms a channel communicating with the combustion chamber of the rotor with the working cavity of the turbine us, in which it has its blades (RU 85559 U1, 10.08.2009 and RU 2393363 C, 27.06.2010 of the same applicant).

In these technical solutions, the engine has not been fully cooled, which negatively affects the reliability of its operation, while the known engine does not disclose the means of synchronizing the operation of the rotor and turbine, which also negatively affects the reliability of the engine.

The technical result of the invention is to increase engine reliability.

The specified technical result was obtained by a gas turbine engine containing a rotor with combustion chambers and a turbine located in the housing, the housing has a cover, the rotor is fixedly connected to the engine shaft, and the turbine rests on the shaft with the possibility of its free rotation around the shaft, the turbine is installed in the turbine housing, the rotor is installed in the rotor housing, rotor housing and turbine are rigidly connected to each other, the rotor combustion chambers are located around the circumference of the rotor and each of them has an opening on one side for supplying a working mixture, and on the other side there is a nozzle, between the rotor and the turbine there is installed a separation disk with windows, each of which forms a channel communicating with the combustion chamber of the rotor with the working cavity of the turbine, the turbine contains a drum located around the shaft and located in the drum a hollow support, which is rigidly connected with the drum and mounted on bearings on the motor shaft with the possibility of rotation around the shaft, the cover of the motor housing has an elongated part along the shaft and installed in it n gearbox, which shaft is coupled with the drum gear means of toothing provided on the rear end portion of the drum cover and the output intermediate shaft gear unit having means for connecting the shaft with the oil pump and the compressor.

A cavity is formed between the outer surface of the drum and the inner surface of the turbine casing for exhaust gas from the turbine blades, an air cooling cavity is formed between the inner surface of the drum and the outer surface of the hollow support to allow cooling air to pass through it, and an oil cavity is formed in the hollow support for passage through it oils.

In the dividing disk, cooling water radial channels and an annular channel connected to each other are made, a central water channel and radial channels extending from it are made in the shaft, windows for cooling water, an annular cavity, radial channels and a water cavity are in communication with each other and with the upper and lower channels in the rotor housing, used to communicate with the pump for supplying water to the engine.

Figure 1 shows a gas turbine engine in longitudinal section;

figure 2 - connection diagram of the compressor with the engine;

figure 3 is a section aa in figure 1;

figure 4 - the rear of the engine with pipes for exhaust gases and cooling air;

figure 5 - the front of the engine with pipes for drainage of oil;

figure 6 is a section bB in figure 5;

figure 7 - connection diagram of the compressor with the engine;

on Fig - connection diagram of the mixer with the engine;

figure 9 - engine cover in cooperation with a compressor and a mixer;

figure 10 - the combustion chamber of the engine with a guide window at the time of the stroke (scan);

figure 11 - position of the combustion chamber at the time of its purge and the fuse of the working mixture (scan);

in Fig.12 is a section bb in Fig.11;

in Fig.13 - the front of the engine with elements of a water cooling system;

on Fig - section GG on Fig 13;

on Fig is a diagram of a water cooling system of the engine;

in Fig.16 - the rotor of the engine in cross section;

on Fig - rotor in longitudinal section;

on Fig - dividing disk of the engine;

on Fig - engine rotor, rear view;

Fig.20 is a rotor of the engine, front view;

in Fig.21 - the back of the front engine cover;

in Fig.22 - place D in Fig.18;

in Fig.23 - the place And in Fig.22;

on Fig - section KK in Fig.23;

on Fig - dividing disk in cross section;

on Fig - section LL in Fig;

on Fig - arrangement of the sealing rings of the rotor;

in Fig.28 - the rotor of the engine in an enlarged view;

in Fig.29 - place M in Fig.28;

on Fig - separation disk and rotor in cooperation;

on Fig - section PP in Fig;

on Fig - scan of the rotor with combustion chambers (left and right sides).

The gas turbine engine contains a rotor 1 (Fig. 1), the turbine described below is installed in parallel with the rotor in the housing 2, a separation disk 3 is installed between the rotor and the turbine. The rotor is located in the housing 4 and is fixedly mounted on the shaft 5, on the end of which a gear wheel 6 is fixed, meshed with the gear of the gearbox described below. The housing 4, the separation disk 3 and the housing 2 of the turbine are rigidly connected to each other.

The engine has a front cover 7, rigidly connected to the housing 4 of the rotor. In the rotor 1, there are many closed by a cover 7 chambers 8 of combustion of the working mixture of fuel. Each chamber 8, when the engine is running, communicates in a predetermined order with guide windows 9 made in the dividing disk 3. Each guide window 9 communicates with a cavity 10 formed by the inner surface 11 of the turbine housing 2.

The engine has a rear cover 12, which closes from the end of the housing 2 of the turbine. Essentially, the cover 12 is a continuation of the engine housing, since it is rigidly connected to the turbine housing 2. Thus, the front cover 7, the rotor housing 4, the separation disk 3, the turbine housing 2 and the engine rear cover 12 in connection with each other form in a rigid engine housing. The engine cover 12 is also a turbine cover. The engine cover 12 has a complex three-dimensional shape, inside of which is located the engine gearbox described below. The shaft 5 is connected via a gear 6 fixed to it with an intermediate shaft 13, which is essentially a power take-off shaft.

In the stationary housing 2 of the turbine is rotatably mounted a drum on which the turbine blades 14 are rigidly fixed. In parallel with these blades, blades 15 are fixed on the turbine housing 2. The turbine is essentially a hollow cylindrical part, conventionally referred to in this description as a drum 16, on the outer surface of which the blades are fixed 14. In the engine embodiment, the blades 14 form rows and the blades 15 are located between the rows of blades 14.

Figure 2 conditionally shows the air ducts 17 for supplying compressed air from the compressor 18 to the engine power system with a working fuel mixture. The compressor may be mounted on the engine frame or it may be located outside the engine frame. As an example of execution in the presented design, the compressor shaft is connected to the intermediate shaft 13 of the gearbox by a coupling.

In the lower part of the rotor casing 4 (Fig. 1), a channel 19 is made for removing hot water from the water annular cavity 20, which is made in the rotor casing 4 and is located around the rotor 1. In the upper part of the casing 4, a channel 19 for removing steam from the water ring is made cavity 20.

The turbine drum 16 has a drum cover 21 rigidly attached thereto having a circular tail portion that is located in a central hole of the engine rear cover 12. In the back cover 12 in its lower part there is a recess forming an oil-filled crankcase 22 of the engine, which is connected by a channel 23 to the engine lubrication system. In the crankcase 22 is located the drive gear 6 of the gearbox, which is meshed by the gears of the gearbox, immersed in the crankcase oil.

The engine has a pipe 24, which is in communication with the air cavity 10 of the turbine. The pipe 24 serves to exhaust the exhaust gases from this cavity. The engine has a pipe 25, which is in communication with the cavity of the drum 16. The pipe 25 serves to drain cooling air from the drum cavity. The engine has an oil pump 26, which is connected by channels 23 and tubes to the lubrication points of the engine. A turbine fan 27 is fixed in the cavity of the drum 16 for pumping cooling air through the engine.

In the separation disk 3 (Fig.6), a fitting 28 is made for supplying cooling water or other cooling liquid to the channel of the disk 3. In the separation disk 3 there are also air intake chambers 29 for air intake from the atmosphere.

The oil pump 26 (Fig. 1) is connected to the countershaft 13 by gears (not shown), the working cavity of the oil pump is communicated by tubes with an oil fitting 30 installed in the front cover 7 of the engine. The fitting 30 is in communication with the lubrication points of the engine, in particular with the bearings of the engine, through the respective channels, from where the oil returns to the oil pump 26 through the oil pipes 31.

Figure 9 shows the fittings 32 for purging the combustion chambers of the engine and the fittings 33 for supplying the working mixture to the combustion chambers screwed into the openings of the front cover 7 of the engine. Figure 9 also shows schematically the igniters 34 or spark plugs of the working mixture, which are located in the threaded holes of the front cover 7. The igniters 34 are located on opposite sides of the rotor 1 (Fig. 11) in the front cover 7 and in the separation disk 3. Fittings 33 ( Fig.9) communicated with the mixer 35 through the diffuser 36. In the mixer, the air is mixed with fuel and the resulting working mixture is supplied under pressure to nozzles (not shown), from where it enters the working chambers 8 through the air ducts 17 (Fig. 1).

Between the front cover 7 of the engine and the separation disk 3 in the housing 4 is made a semicircular recess 37 (Fig.13), located around the rotor 1 and around the combustion chambers 8 of the rotor. Each rotor combustion chamber 8 (FIG. 10) has a nozzle 38 communicating with the turbine cavity 10 during its rotation, in which the turbine blades 14 are located.

In the rotor there are channels 39 for circulating water in them of the cooling system of the combustion chambers 8 and the engine, and in the separation disk 3 channels 40 are made for circulating in the water disk 3 of the cooling system of the separation disk and the engine. The channels 40 are used to cool the separation disk 3 and its windows 9, while the channels 40 are in communication with the channels 19 (Fig. 13) of the engine water cooling system. The annular cavity 20 is located on the periphery of the rotor 1 between the front cover 7 of the engine and the separation disk 3. The water cooling system also includes many channels for the passage of water under pressure from the following water pump, which is installed separately from the engine or on the engine and kinematically connected with motor shaft 5.

The engine has a gearbox, the driving gear 6 of which (Fig. 1) is mounted on the shaft 5 and is engaged with the gear 41 (Fig. 4), which is made in the block with the gear 42, betraying rotation from the turbine drum 16, through the gear ring 43 which is made at the end of the round tail portion of the cover 21.

The separation disk 3 through the upper ducts 17, shown in Fig. 8, is connected with the fittings 32 and with the compressor 18, which supplies air to the combustion chambers of the rotor, while the separation disk has air purge channels 44 (Fig. 12) for purging the combustion chambers 8 rotor after combustion of the working mixture. Through channels 44, gas is vented to the atmosphere.

The drum 16 of the turbine 2 includes a tubular part connected to it, conventionally referred to in this description as a tubular support 45 (Fig. 1), which is supported by bearings mounted on the motor shaft 5. The support 45 is called the support because it serves to support the drum 16. The support 45 is mounted on bearings on the motor shaft 5 as shown in FIG.

Thus, the turbine includes a support 45, a drum 16 which is rigidly connected to it, and blades 14 fixed to the drum, while these elements are mounted to rotate around the shaft 5.

Between the inner surface of the support 45 and the surface of the shaft 5 there is formed an oil-filled cavity in communication with the engine lubrication system. This cavity serves to circulate oil in it, which serves to lubricate and cool the bearings.

The support 45 and the drum 16 are rigidly connected to the drum cover 21 and together with it constitute a single unit supported by bearings, while the cavity of the support 45 is elongated, such as that shown in FIG. 1, and the motor shaft 5 is located in this cavity moreover, the cavity of the support 45 is made in the form of a bell, tapering towards the rotor 1.

In the dividing disk 3 (Fig. 14), an annular channel 46 is made, which communicates with the radial channel 47 of the dividing disk 3. (47 also shows the radial channel of the rotor included in the general engine water cooling system.

FIG. 15 shows a water tank 48, a radiator 49 connected to it, with which channels 19 of a water cooling system are connected. A water pump 50 is connected with a capacity 48, which is connected by a pipe to the fitting 28 (Fig. 6) for supplying water to the separation disk 3.

The oil drain channel 30 (Fig. 1) is in communication with the oil channels 51 (Fig. 17) and oil cavities made in the form of annular grooves 52 in the rotor 1.

Oil scraper rings 53, 54 and 55 (Figs. 23, 27) and o-rings 56 and 57 are located in the grooves of the rotor 1. In the rotor around the shaft 5 there is an annular cavity 58 (Figs. 1, 5) for circulating water in it for cooling the rotor . An annular recess 59 (Fig. 25) is made in the separation disk for water to pass through it. In the front cover 7 (Fig. 28), a channel 60 is provided for supplying oil to the bearing in which the shaft 5 is mounted. In front of the front cover 7 there is a tube 61 for removing oil from the shaft bearing 5. Fig. 29 shows a chamfer 62 for collecting and dumping oils. The rings 53-55 installed between the front cover 7 and the rotor 1 are pressed against the surface of the cover by springs 63 or, as an option, copper-asbestos gaskets.

The gearbox is closed by a cover 64 (Fig. 1), rigidly connected to the cover 12. The shaft 5 is installed in the said bearings 65 located in the seats of the covers 64, 12 and 7.

In the rotor 1, on the front side of each combustion chamber 8, a nozzle 66 is made (Fig. 10) for supplying the working mixture to the combustion chamber and for purging the chamber after the working mixture is burned therein.

In Fig.30 shows the working surface 67 of the separation disk 3, facing the surface of the rotor 1, and Fig.31 shows the bevel 68 of the oil scraper ring 54.

Thus, the engine contains a mechanical part made of the above-mentioned elements interconnected, and it also has an engine air cooling system including all elements that facilitate the movement of air in the engine, in particular, a fan 27 mounted on a support 45, a turbine 16, channels 29 of the separation disk 3 (Fig.25), as well as the air cavity 69 (Fig.1) located between the drum 16 and the support 45.

The engine also contains a water cooling system, which includes a tank 48 (Fig. 15), a water pump 50, a channel 70 in the separation disk 3 (Fig. 14), and an annular channel 46, as well as radial channels 71 made in the shaft 5 (Fig. .1) and the central channel 72. The radial annular cavity 58 (Fig. 14), radial channels 47, channels 73 (Fig. 1) communicating the annular water cavity 20 with channels 39 for circulating system water therein also enter the water cooling system cooling the combustion chambers, as well as other channels and cavities formed by engine elements.

The engine also includes a lubrication system, which includes an oil pump 26 (Fig. 1), an oil channel 23, an axial channel 74 and radial channels 75 in the shaft 5, as well as a cavity 76 between the shaft 5 and the inner surface of the support 45. The lubrication system also has other, not named channels and cavities formed by engine elements.

The engine operates as follows. The engine is launched into operation by a starter (not shown) by rotation of the shaft 5 with the starter, which at the same time rotates the intermediate shaft 13 of the engine through gears 41 and 6. From the rotation of the shaft 13, the shaft of the compressor 18 starts to rotate (Fig. 2), which supplies air to the engine under high pressure on the upper ducts 17 high pressure. In the lower ducts 17, air under low (conditionally) pressure is supplied to the mixer 35 (Fig. 8), where it is mixed with fuel. The resulting working mixture is fed into the combustion chamber 8, which is in position P2, which is shown in the scan of the rotor in Fig.11. When the rotor is rotated by a certain angle, the camera 8 moves to position P3. When this occurs, the fuse of the working mixture in the combustion chamber 8 in its position PZ. The working mixture burns, the combustion products of the mixture make a working stroke of the rotor 1 and it rotates together with the shaft 5 by a certain angle.

The working stroke of the rotor occurs at the moment when the rotor nozzle 38 is combined with the window 9 of the separation disk 3 (Fig. 10) and the combustion products of the working mixture from the combustion chamber 8 fall onto the turbine blades 14, which starts to rotate, while the starter is turned off. The combustion products of the working mixture also pass through the turbine blades 15, which are stationary and perform the functions of guide elements for the passage of the combustion products from the rotor 1 to the cover 12. In the same way, the combustion of the working mixture in other combustion chambers of the rotor takes place.

When the engine is running, the combustion products pass all the turbine blades 14 and exit in the form of exhaust gas through pipes 24 (Fig. 1) into the atmosphere. In this case, the rotor and turbine rotate in the same direction.

Together with the turbine, a fan 27 rotates, which, through nozzles 29 (Fig. 6), draws air from the atmosphere and drives it inside the turbine drum 16, cooling the drum and turbine. Cooling air enters the atmosphere through pipes 25. The combustion chambers (Fig. 32) operate in a certain sequence. If the KS-1 combustion chamber is filled with its working mixture, then the KS-2 combustion chamber fuses the working mixture, while in the KS-3 combustion chamber the combustion of the working mixture takes place, and the combustion products of the KS-4 combustion chamber come out under high pressure and fed into the guide window 9 (figure 10) and, further, on the blades 14 of the turbine 2. During one cycle of operation of the rotor, the KS-5 combustion chamber is blown with air. Then the described process is repeated.

Lubrication of the engine is as follows. From the crankcase 22, oil is pumped by a pump 26 through a channel 23 to all rubbing surfaces of the engine and bearings 65 (Fig. 1). Through the bearings, oil enters the cavity of the support 45, then to the rear (left in the drawing) bearing 65 and through the gaps between the gear ring 43 and the shaft 5, the oil again enters the crankcase 22. The oil lubricates and cleans the friction surfaces of the engine, receives heat from them and cools these surfaces. The surface 67 of the separation disk (Fig. 30) adjacent to the surface of the rotor is constantly cleaned with an oil scraper ring to prevent burnout of the oil during the period when the process of combustion of the working mixture is in the combustion chambers. At the same time, an oil film is constantly applied to the surface 67 from the oil emanating from the annular groove 52 (Fig. 27). From the fitting 30 (FIG. 1), oil enters the front annular groove 52, then into the channel 51, then into the rear annular groove 52 (FIG. 28), filling the entire annular groove 52 (FIG. 17). Getting on the o-ring 56 (Fig.27), the oil is collected in the groove 62 of the rotor 1, reaches the channel 31 (Fig.29) and merges into the pipe 61 to drain the oil (Fig.28 and 29). The chamfers on the rings 53 and 54 (FIGS. 30 and 31), as well as the chamfer 68, the oil is removed from the friction surfaces that are outside of each nozzle 38 of the rotor combustion chamber. As a result, oil burnout is excluded.

When the engine is running, it is air-cooled. A fan 27 (Fig. 1) from the atmosphere takes a cooling (cold) air through the channels 29 of the separation disk (Fig. 25). Cooling air enters the blades 14 of the turbine 2, runs along the entire length of the air cavity 69 (Fig. 1), which is located between the drum 16 and the support 45, while the length of the air cavity 69 allows you to effectively blow and cool the elements of the turbine 2. The cooling air is heated and through the elongated air cavity 69 (Fig. 1) and the pipe 25 it leaves heated into the atmosphere and carries heat from the hot elements of the turbine.

When the engine is running, its water cooling is also carried out, for this, through the nozzle 28 (6) through radial channels 47 in the separation disk 3 (1), water is pumped 50 (Fig. 15) into the annular channel 46 (Fig. 14) and it falls into the Central channel 72 of the shaft 5 (figure 1). Through the channel 72, water enters the annular cavity 58 (Fig. 5) and through the radial channels 47 of the rotor, the water enters the windows 39 of the rotor and the channels 73 (Fig. 1). Next, the water enters the water cavity 20, then steam leaves the water through the upper channel 19 and enters the radiator 49 (Fig. 15), and through the lower channel 19 (Fig. 1), leaving the rotor, into the radiator 49 (Fig. 15 ) water enters. The radiator is blown by a fan 77, while in the radiator the water is cooled and drained into a container 48 (Fig. 15). In the process of the described engine cooling cycle, water from the nozzle 28 (Fig.6) also enters the annular water channel 46 and through the channels 47 of the separation disk 3 (Fig.13), the water enters the window 40 (Fig.10, 13). Then, the water through the channels 19, passing into the tube (Fig.13), is supplied to the radiator 49 (Fig.15). At the same time, through the lower channel 19, departing from the separation disk 3 (Fig. 13), water enters the radiator 49 (Fig. 15), is cooled in it and is discharged into the container 48 (Fig. 15).

Compared with the known technical solutions, the technical solution presented in this description eliminates jamming of the rubbing surfaces of the engine, since it provides for more efficient cooling of the rotor, turbine and separation disk, which significantly increases the reliability of the engine as a whole.

Claims (3)

1. A gas turbine engine, characterized in that it contains a rotor with combustion chambers and a turbine located in the housing, the housing has a cover, the rotor is fixedly connected to the engine shaft, and the turbine rests on the shaft with the possibility of its free rotation around the shaft, the turbine is installed in the turbine housing , the rotor is installed in the rotor housing, the rotor housing and the turbine are rigidly connected to each other, the rotor combustion chambers are located around the circumference of the rotor and each of them has an opening on one side for supplying the working mixture to it, and on on the other side there is a nozzle, between the rotor and the turbine there is installed a separation disk with windows, each of which forms a channel communicating with the combustion chamber of the rotor with the working cavity of the turbine, the turbine contains a drum located around the shaft and a hollow support located in the drum , which is rigidly connected with the drum and mounted on bearings on the motor shaft with the possibility of rotation around the shaft, the motor housing cover has an elongated part along the shaft and a gearbox is installed in it, Al of which is connected by a gear to the drum by means of a ring gear made at the end of the tail of the drum cover, and the output intermediate gear shaft has means for connecting this shaft to the oil pump and compressor. 2. The gas turbine engine according to claim 1, characterized in that a cavity is formed between the outer surface of the drum and the inner surface of the turbine housing to exhaust exhaust gas from the turbine blades, and an air cooling cavity is formed between the inner surface of the drum and the outer surface of the hollow support to allow the cooling passage through it air, and an oil cavity is formed in the hollow support for oil to pass through it. 3. The gas turbine engine according to claim 1, characterized in that the cooling water radial channels and the annular channel communicated to each other are made in the separation disk, the central water channel and the radial channels extending from it are made in the shaft, the windows for cooling water are made in the rotor, the ring cavity, radial channels and a water cavity in communication with each other and with the upper and lower channels in the rotor housing, which serve to communicate with the pump for supplying water to the engine.

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