RU2393363C1 - Gas turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises rotor with combustion chambers and turbine rigidly fitted on the shaft arranged inside the housing. 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. Rotor and turbine hollow shaft allows compressed air to flow from compressor there through. Separating disk with elongated openings arranged on opposite sides of the axis of symmetry is mounted in the housing between rotor and turbine and rigidly coupled with the housing. Multiple blades are arranged in every said opening all along its length, coupled with said separating disk or made integral with it, for example cast as a single piece. Every blades of said separating disk represents a section bent along housing cross section that makes with adjacent blade section aforesaid passage for compressed gas to flow from combustion chamber to turbine blades. One end of said air passage is directed towards rotor combustion chamber. Opposite end of said passage runs towards turbine blades. Axis of nozzle of every combustion chamber is inclined to combustion chamber crosswise axis.

EFFECT: higher engine efficiency, its power and simplified design.

13 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 Power Publishing House ", M., L., 1948, p. 37; Ya. I. Schnee" Gas Turbines "," Mashgiz "., M., 1960, p.11 - copies rilagayutsya).

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 on its periphery (RU 2147341 C1, 2000.04.10. RU 2096639 C1, 1997.11.20., RU 2282734 C2, 2006.08.27., 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.

The technical result of the invention is to increase the efficiency of the engine, its power and simplify the design.

The specified result was obtained by a gas turbine engine containing a rotor located in the housing with combustion chambers and a turbine that are rigidly mounted on one shaft, while 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 on the other side - the nozzle, the rotor shaft and the turbine are hollow with a cavity for air to pass through it from the compressor, in the case between the rotor and the turbine there is a separation disk rigidly connected to the body with the opposite and from the axis of symmetry of the disk with elongated windows, in each window along its length there are many blades associated with the separation disk or made with it at the same time, for example, cast together with the separation disk, each blade of the separation disk is made in the form of a profile curved in the transverse plane of the casing, forming with the profile of the adjacent blade of the separation disk, an air channel for passing gas through it from the combustion chamber of the rotor to the turbine blades, with one end of each specified air channel side of the nozzle of the combustion chamber of the rotor, the other end of each air channel is directed towards the blades of the turbine, and the axis of the nozzle of each combustion chamber is inclined to the transverse axis of the combustion chamber.

1 shows a sectional view of an engine;

figure 2 is a fragment of the engine in an enlarged view;

figure 3 is a section aa in figure 1;

figure 4 is a separation disk of the engine;

figure 5 is a section bB in figure 4;

figure 6 - the rotor of the engine;

Fig.7 is a view In Fig.6;

in Fig.8 is a view of G in Fig.6;

figure 9 is a section DD in figure 7;

figure 10 is a cross-section EE in figure 8;

figure 11 - arrangement of the combustion chambers of the rotor in side view;

on Fig - fuel engine systems;

on Fig - engine lubrication system.

The gas turbine engine comprises a rotor 1 (Fig. 1), in parallel with which a turbine 2 is installed in the engine casing. The rotor and turbine are in communication with the compressor 3. The gas turbine engine casing 4 includes a front cover 5 and a rear cover 6 that are rigidly connected to it.

The engine turbine 2 has a plurality of vanes 7 (FIG. 2), the engine casing 4 has a plurality of vanes 8 that are located in the casing, between the turbine 2 and the rotor 1 there are a plurality of guide vanes 9 (FIG. 3) of the dividing disk.

Each blade 9 is made in the form of a profile rounded on both sides with streamlined surfaces on its opposite sides. All blades 7-9 are arranged in such a way that they create an air corridor for the movement of gases from the combustion chambers of the rotor into the pipes 10 for the removal of gases from the motor housing 4. The direction of movement of the gases from the combustion chamber of the rotor is shown in Figs. 1-3 by dashed lines with arrows.

The blades 9 (Fig. 3) are fixed in two elongated windows that are opposite in the separation disk 11 with respect to the axis of the shaft 12. The vanes 9 are connected to the separation disk 11 and are located along the entire length of each window. Preferably, the blades 9 are made in the windows of the separation disk 11 integral with the separation disk and are obtained, for example, by casting the separation disk together with the vanes. The separation disk is rigidly connected to the housing 4 by its peripheral part. In the center, the separation disk 11 has a central hole through which the hollow shaft 12 of the engine passes. A gap is formed between the central hole of the separation disc and the hollow shaft 12. In fact, the separation disk 11 is also part of the housing 4, since it is rigidly connected to the housing 4 and separates the housing from the inside into the rotor cavity and the turbine cavity, in which the rotor 1 and the turbine 2 are respectively located. The latter are rigidly fixed to the common hollow shaft 12, which mounted in front and rear covers 5 and 6 on rolling bearings. The air cavity of the shaft 12, indicated below, is made along the shaft along its axis, in communication with the radial air channels of the turbine 2 and serves to supply cooling air through it to the engine from the compressor 3.

The gas turbine engine has air ducts 13 (FIG. 12) for supplying the working mixture to the combustion chambers of the rotor. The working mixture is ignited by glow plugs 14 in the combustion chambers 15 of the rotor, which are located in it along its circumference closer to the peripheral part, while the working mixture is supplied to the chambers using a compressor 3, the shaft 16 of which is connected to the motor shaft 12 to synchronize their operation ( in one engine version). In another embodiment of the engine, arranged, for example, in the form of a gas turbine installation, the compressor and rotor shafts are disconnected, and the compressor operates independently of the rotor 1 and engine turbine 2.

The motor housing 4 has a pipe 17 (FIG. 1) for removing the cooling air of the rotor, and for removing cooling air from the turbine 2, the air cavity 18 of the shaft 12 and the air channels 19 connected with it (FIG. 1) with radial and horizontal sections are used. The air cavity 18 of the shaft 12 is in communication with the air cavity of the shaft 16 of the compressor 3 (the position of the cavity of the shaft 16 is not shown). Through the cavity of the shafts 12 and 16, cooling air is supplied to the turbine 2. The housing 4 also has channels 20 for supplying lubricant to the engine.

The fuel working mixture is formed in the mixer 21 (Fig. 12), where the fuel is mixed with air and converted into a working mixture, and through the air ducts 13 and 22, the working mixture is supplied to the combustion chambers 15 of the rotor 1.

The lubrication system (Fig. 13) includes an oil pump 23 in communication with the channels 20 (Fig. 1) of the lubrication system leading the oil to the rubbing surfaces of the engine, as well as the other channels mentioned below.

The gas turbine engine comprises a water cooling system (Fig. 5), including pipelines for supplying water to the engine and a pipe 24 for outputting water used in the cooling system from the engine. This water cooling system is described below.

The engine contains an air system (Fig. 12) for purging the combustion chambers 15 of the rotor, which includes fittings or openings 25 of the nozzles for supplying air to the combustion chambers, which are in communication with the air ducts 26-29, while the air duct 29 (Fig. 1) also serves to supply cooling air to the rotor 1 and turbine 2. These fittings are mounted on the cover 5 of the engine housing.

In addition to the indicated means of blowing the combustion chambers of the rotor 1 and means of air cooling of the rotor and turbine, the air system includes radial air channels 30 (Fig. 9) made in the rotor and horizontal air channels 31 for the passage of cooling air through the rotor 1, while for exiting the turbine exhaust cooling air into the atmosphere there is a pipe 32 (figure 1).

The lubrication system, in addition to the above-mentioned elements, also contains oil pipelines 33 (Fig. 13), a fitting 34 (Fig. 1) for supplying oil, and oil pipelines 35 (Fig. 13) for draining oil to the engine sump 36 or to the drain tank.

The fuel system (Fig. 12), in addition to the already mentioned elements, contains high-pressure pumps 37, which are in communication with the nozzles 38, swirlers 39, connected with the diffusers 40 and nozzles, and also the pipe 41 of the compressor 3, in communication with the air ducts 42 for supplying air into the mixers 21.

The rotor is made of annular grooves 43 and 44 (Fig.6) with O-rings 45 and 46 located in them (Fig.2) for sealing the gaps 47 between the rotor 1, the front cover 5 of the housing and the separation disk 11.

The gas turbine engine is equipped with a capacity 48 (figure 5) with a cooling liquid in it, an electric motor 49, connected to a pump 50 for supplying a cooling liquid. The pump is in communication with a capacity 48, which is in communication with a radiator 51, next to which is located an electric fan 52.

All of the above engine components, including its housing, are preferably arranged on the same frame. In the case of the location of the nodes of these engine systems on separate frames, including a compressor, the engine with its power, cooling and lubrication systems is converted into a gas turbine unit with large power and large dimensions.

It follows from the foregoing that a feature of a gas turbine engine is that there is a dividing disk 11 (Fig. 1) between the rotor 1 and the turbine 2, which separates the space of the rotor casing into two cavities, in one of which the rotor is located, and in the other cavity a turbine, moreover, between the indicated body cavities in the separation disk, on the sides opposite from the shaft axis, the windows described below are made. Guide vanes 9 are located along the length of each window (FIG. 3), each of which has a cross-sectional profile in cross section, forming a curved channel with an adjacent identical blade shape for gas to move through it toward the turbine blades 7 (FIG. 1). The shape of each guide vane 9 and the bending angle of its rounded surfaces are selected from the condition of rotation of the turbine in the direction of rotation of the rotor. This condition meets the shape of each combustion chamber 15 and its location in the rotor, as well as the direction of the nozzle that each combustion chamber has.

The shape of the combustion chamber 15 (FIG. 3) is spherical and on the one hand the chamber has an inlet 53 located on the transverse axis 54 of the combustion chamber 15, which is located across the rotor 1, and on the other hand the chamber has a nozzle 55, the axis 56 of which is inclined at an angle α to the transverse axis 54 of the camera.

Adjacent vanes 9 of the separation disk 11 form air channels 57 (FIG. 3) for the passage of gas through them from the combustion chambers of the rotor to the blades 7 of the turbine. The blades 9 have profiles curved in the transverse plane of the casing, forming the aforementioned air channels 57, with one end of each specified air channel 57 (its lower end in FIG. 3) directed towards the combustion chamber 15 of the rotor 1, in particular towards the nozzle 55 of the chamber combustion, and the other end of each air channel 57 (its upper end in FIG. 3) is directed towards the blades 7 of the turbine 2. In the cover 5, openings 58 are made, which serve to supply the working mixture to the chambers.

At least two of the aforementioned windows 59 are made in the separation disk, which are identical in shape and are located symmetrically on both sides of the axis of symmetry of the separation disk. The shape of these windows is not disclosed in the description, however, it should be noted that the elongated longitudinal sides of each window 59 on the rotor side are made over a large radius, are located opposite each other and parallel to each other, and the other two opposite sides of the window are made at a smaller radius equal to the radius of the nozzle 55 in the view from the side of the separation disk, with blades 9 fixed or made in each window 59. It should be noted that each window in the separation disk is conventionally shown by several positions 59 in FIG. 3, since Ti, the window along its length with blades 9 is divided into many windows 59, forming one window.

A gas turbine engine in its one embodiment, when the rotor shaft of the engine is connected to the compressor shaft, as shown in FIG. 1, operates as follows. Rotate simultaneously the shaft 12 of the engine and the shaft 16 of the compressor 3 with a starter (not shown). In this case, air from the compressor 3 through the air ducts 42 (Fig. 12) is supplied to the mixers 21, where it is mixed with fuel, and the working mixture enters through the air ducts 13 through the openings in the front cover 5 and the openings 53 (Fig. 3) into the combustion chambers 15 rotors that are located on opposite sides of the axis of the shaft 12 or from the axis of symmetry of the spacer disc 11. During the supply of the working mixture, the process of filling these combustion chambers 15 occurs, and this process occurs when the holes 53 (Fig. 1) of each chamber 15 are combined with the holes 58 that perform They are in the cover 5 of the engine casing and communicated with the air ducts 13 through the openings 25 of the fittings connecting the air ducts to the cover. With further rotation of the rotor, the hole 53 of each chamber 15 is closed by a cover 5 and the working mixture in the chamber 15 is closed. In this case, the working mixture in two chambers is simultaneously ignited by glow plugs 14 (Fig. 12). At the same time, when the rotor rotates, the nozzle 55 (Fig. 3) of each chamber is combined with the window 59 of the separation disk 11 and the blades 9 located in this window along its entire length 9. Gas from the two chambers 15 simultaneously after the fuel is burned into them through nozzles 55 and windows 59 first onto the stationary blades 9 of the separation disk 11, and then onto the movable blades 7 of the turbine 2. Gases flow around the profiles of the blades 9 and, passing between them, change the direction of movement in accordance with the profiles, act on the blades 7 of the turbine in the direction of rotation of the rotor . The turbine 2 rotates from the action of gases and transfers the torque to the shaft 12, while a reactive force arises from the movement of gases from the combustion chambers on the rotor.

Further, when combining the openings 53 of the chambers 15 with other openings 25 (Fig. 12) of the fittings of the air supply system to the combustion chambers, the working chambers 15 are purged and then the described cycle of operation of the second group of combustion chambers is repeated, with each rotation of the shaft and rotor in each the rotor combustion chamber is the combustion of the working mixture twice.

When the engine is operating, the shaft 12 rotates in the direction of rotation of the rotor 1, turbine 2 and shaft 16 of the compressor 3, while the systems for supplying the working mixture to the chambers, purging the combustion chambers, lubrication, air and water cooling of the engine provide the engine synchronous stable operation, while it is possible rotations of the rotor and turbine in one direction, when the moments of inertia of the rotor and turbine masses rotating in the same direction are summed. Significantly reduced mechanical power losses due to friction of the transmission elements of the rotor and turbine rotation in the specified direction due to the fact that the use of such elements in an engine of this type is not required. The engine design is greatly simplified, the operation of all engine elements is synchronized, each combustion chamber has its own gas outflow channel, which ensures, when the rotor rotates, combustion of the working mixture in the chamber when it is closed, and purging of the channel behind the cooling chamber closed by the chamber. The space of the specified channel for the outflow of gas from the chamber, communicating with the space in which the blades 7 of the turbine 2 are located after the chamber is purged, is free of gas and cooled. This provides an efficient process for cooling the rotor, the separation disk and the turbine, and the channel freed from gas, passing through the closed combustion chamber does not create resistance to rotation of the turbine 2 and rotor 1, which significantly increases the efficiency and engine power.

Claims (1)

A gas turbine engine containing a rotor in the housing with combustion chambers and a turbine that are rigidly mounted on one shaft, the combustion chambers being 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 the nozzle, the shaft of the rotor and turbine is made hollow with a cavity for the passage of air from the compressor through it, in the case between the rotor and the turbine there is a separation disk rigidly connected to the body with an elongation opposite to the axis of symmetry of the disk By means of windows, in each window along its length there are many blades connected with the separation disk or made at the same time, for example, cast together with the separation disk, each blade of the separation disk is made in the form of a profile curved in the transverse plane of the casing, forming with the profile of an adjacent blade of the separation disk, an air channel for passing gas through it from the rotor combustion chamber to the turbine blades, with one end of each specified air channel directed towards the nozzle of the chamber rotor, the other end of each air channel is directed towards the turbine blades, the axis of the nozzle of each combustion chamber is inclined to the transverse axis of the combustion chamber.

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