A rotary vane internal combustion engines

 

(57) Abstract:

Engines related to energy, transport, mechanical engineering and can be used as a transport and stationary internal combustion engines. Engines contain bypass valves 7, 9, installed in slots 5. In the first engine combustion chamber formed by the wall of the socket and the end cavities of one of the relief valves and consists of two compartments 10, 11. On the side of each compartment made the cut for the intake and exhaust of the working fluid. The second gas turbine engine consists of two sections. In the first section of the working body is served in an external combustion chamber. In the second section of the combustion products impinges on the rotor blades. The third engine consists of three sections and equipped with a condenser and steam generator. In the first section the working fluid is fed into the combustion chamber, the second combustion products impact on the blade, and the third steam generated by heating of the water acts on the blade. These characteristics of internal combustion engines allow you to create compact and material design. 3 S. p. f-crystals, 18 ill.

The invention relates to energy, transport, mechanical engineering and can be the n rotary-vane internal combustion engine, including a housing with a cooling jacket, a bypass valve installed in the sockets, and the combustion chamber of a working body (see patent England 795898, CL F 01 C 1/20, 1958).

Rotary-vane internal combustion engine includes a bypass valve installed in the slots, and a built-in combustion chamber consists of two compartments, in which the combustion of the working fluid. The engine differs in that the combustion chamber formed by the wall of the socket and the end cavities of one of the bypass valves on the side surface of each compartment is made cutout for the inlet of the working fluid.

The problem to which the invention is directed, is the creation of economical, compact and less material-intensive rotary-vane internal combustion engine.

Gas turbine is a rotary-vane internal combustion engine includes a bypass valve installed in the sockets, and the combustion of the working fluid. Gas turbine engine characterized in that it consists of two sections, the first gripping and feeding the working fluid in the combustion chamber, and the second affecting the combustion products on the blades of the rotating rotor, each of which includes a part circular controlname with outlet box of the first section and the inlet window of the second section.

The problem to which the invention is directed, is the creation of compact, cost-effective and less resource-demanding gas turbine of a rotary vane internal combustion engine (RLDS).

RLDS with heat recovery circuit includes an annular channel, a bypass valve installed in the sockets, the combustion of the working fluid. RLDS differs in that it consists of three sections and equipped with a condenser and steam generator. A combustion chamber connected to the inlet pipe with the first section and the discharge pipe with the second section and the inlet steam line from the third section and the water with steam.

The problem to which the invention is directed, is to create an economical, compact and highly efficient rotary-vane internal combustion engine (RLDS).

In Fig. 1 is given a rotary vane internal combustion engine; Fig. 2 is a cross section along a-a in Fig. 1; Fig. 3 - bypass valve of Fig. 4 is a view along B in Fig. 3; Fig. 5 is a view In Fig. 3; Fig. 6 is a view along G in Fig. 3; Fig. 7 - bypass valve of Fig. 8 is a section along d-D in Fig. 7; Fig. 9 is a view E of Fig. 7; Fig. 10 - work RLDS with a built-in combustion chamber - the first phase of Fig. the Rania - the third phase of Fig. 13 - unit gas turbine RLDS; Fig. 14 - a three-section device RLDS; Fig. 15-unit four-section RLDS; Fig. 16 is a three - section device RLDS with heat recovery circuit of Fig. 17 - gas turbine RLDS multi-stage; Fig. 18 is the same, the section f-F in Fig. 17.

RLDS (Fig. 2) with built-in combustion chamber includes an annular channel 1, is divided into two working sections, and a rotor with three blades 2, 3, 4.

The first working section is designed to supply the working fluid in the internal combustion chamber located in the socket 5, and includes an inlet window 6 and the bypass valve 7.

The second working section is designed to transmit torque to the rotor shaft under the influence of combustion products on the blade, includes exhaust port 8 and the bypass valve 9.

By-pass valve 7 (Fig. 2) and 9 (Fig. 2) for bypass blades have two lateral cavity 17. The ratio of their mutual rotation of the rotor is taken as 3:2.

The length of the cylindrical part of the valve 7 (compared with valve 9) is increased by the depth arranged in its end parts of the two cavities 10 and 11, which together with the side wall of the socket 5 is formed by two otsesti has holes 12 and 13, through which the inlet (release) camera (camera) of the working fluid.

Open socket connection 5 with the annular channel 1 is increased by reducing the working surfaces 14 and 15 to the minimum size, providing closure of the annular channel from the flow of the working fluid at any angular position of the valve 7.

Full working cycle of this RLDS consists of cycles of each blade. The duty cycle of each blade is for one revolution of the rotor and is divided into four phases (discussed on the example of the blade 2 and the camera 10): the first phase (Fig. 10) move the working fluid at the site of the stroke of the first section under the influence of the blades 2 and enters into the chamber 10 (in rotation by-pass valve, the cut-out 12 out from behind the working surface 14, opening up access to the working body); the second phase (Fig. 11) - combustion and partial combustion of the working fluid in the closed chamber 10 during the bypass blades (cut closed 12 working surface 15); the third phase (Fig. 12) move the blade 2 on the site of the stroke of the second section under the influence of combustion products flowing from the chamber 10 through the notch 12, which is open towards the

In the implementation of the next working cycle of the blade 2 communicates with the chamber 11.

Gas turbine RLDS (Fig. 13) includes an annular channel 18, is divided into two working sections, a rotor with three blades 19 and 21 and the combustion chamber 22.

The first working section is designed to supply the working fluid into the combustion chamber includes an inlet 23 and outlet 24 open, the bypass valve 25.

The second working section is designed to transmit torque to the rotor shaft under the influence of combustion products on the blade includes an inlet 26 and outlet 27 open, the bypass valve 28.

The operation of the gas turbine RLDS as follows:

the air coming into the first section through the suction box 23 is compressed and through the outlet 24 of the box and the pipe 29 is fed into the combustion chamber 22, which produces fuel combustion.

the combustion products through the nozzle 30 through the suction box 26 rush the second section, where, acting on the blades 19 - 21, result in rotation of the rotor and through the exhaust box 27 go outside.

The proposed gas turbine RLDS can be performed with any number of working sections and steps, as example of which is given:
the s and the rotor 5:1, where the first (bypass valve 36, the inlet 37 and outlet 38 of the window ) and the second (bypass valve 39, the outlet 40 and outlet 41 of the window sections are used to move the working fluid (compressed air) and feeding it into the combustion chamber 45. The third bypass valve 42, the inlet 43 and outlet 44 of the window) to transfer torque to the rotor shaft under the influence of combustion products on the blade.

four RLDS (Fig 15) having six blades against mutual rotation of the bypass valve and the rotor 6:1, where the first (spill valve 54, the inlet 55 and outlet 56 of the window) and the third (the bypass valve 57, the inlet 58 and outlet 59 of the window sections are used to move the working fluid (compressed air) and feeding it into the combustion chambers 60 and 61, the second (bypass valve 62, an inlet 63 and an outlet 64 of the window) and fourth (bypass valve 65, the inlet 66 and outlet 67 of the window) to transfer torque to the rotor shaft under the influence of combustion products on the blade.

RLDS can be used with heat recovery circuit (TUK), which is intended for the use of thermal energy radiated by the walls of the annular channel, and exhaust gases. RLDS is a closed steam to the P> The simplest RLDS with TUK (Fig. 16), as steam engines which used working section includes an annular channel 68 with three sections, the combustion chamber 69, a capacitor 70, the steam generator 71, the inlet 72 to the outlet 73 74 and exhaust, the pipes, the inlet 75 and outlet 76 steam pipes and water pipe 77.

The first (bypass valve 78, the inlet 79 and the outlet 80 of the window) working section is used for supplying the working fluid through the supply pipe 72 into the combustion chamber 69.

The second (bypass valve 81, the inlet 82 and outlet 83 of the window) to transfer torque to the rotor shaft under the influence of combustion products flowing from the chamber 69 to the outlet pipe 73.

The third bypass valve 84, the inlet 85 and outlet ports) for transferring torque to the rotor shaft under the influence of steam flowing from the steam generator 71 downstream steam line 75.

Work RLDS with the FAT, as the steam engine which used the working section, is as follows: in the first and second sections are mode LDVS (description given above), after which the products of combustion from the second section of the exhaust pipe 74 into the steam generator 71; in the steam generator, the water prodenia working section of the third section of the steam enters the condenser 70, where is converted to water and water 77 enters the steam generator.

In one case can be combined in several gas turbine RLDS (multi RLDS) with a common rotor and mechanism kinematic relations (see Fig. 17 and 18), which shows a two-stage (stage I and II) gas turbine RLDS.

Two gas turbine RLDS is the ratio of the mutual rotation of the bypass valve and the rotor is equal to 3:1.

Gas turbine RLDS provided with a common rotor 92 and the mechanism kinematic connection 93 and has at each stage of the two inlet 94, 95 and two exhaust 96, 97 Windows, two slots 98 and 99 with the bypass valves 100 and 101, and three blades 102, 103 and 104.

1. Rotary-vane internal combustion engine, containing the bypass valves are installed in the slots, and a built-in combustion chamber consists of two compartments, in which the combustion of the working fluid, characterized in that the combustion chamber formed by the wall of the socket and the end cavities of one of the bypass valves on the side surface of each compartment is made cutout for the inlet and outlet of the working fluid.

2. Gas turbine is a rotary-vane internal combustion engine, with which it consists of two sections, first, gripping and feeding the working fluid in the combustion chamber, and the second affecting the combustion products on the blades of the rotating rotor, each of which includes a part of the annular channel, the inlet and outlet ports and a bypass valve to the combustion chamber is made detachable and connected by pipes with outlet box of the first section and the outlet window of the second section.

3. Rotary-vane internal combustion engine with heat recovery circuit containing the bypass valves are installed in the slots, a combustion chamber, characterized in that it consists of three sections and equipped with a condenser and steam generator, the combustion chamber connected to the inlet pipe with the first section and the discharge pipe with the second section, the steam generator is connected to the exhaust pipe with the second section and the inlet steam line with the third section, a condenser connected to the outlet steam from the third section and the water with steam.

 

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