RU2661418C1 - Turbocharger thermal machine operating on a closed thermodynamic cycle with internal heat recovery - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: turbocharger thermal machine operating on a closed thermodynamic cycle with internal heat recovery, consists of a radial compressor and a turbine, there are mobile moving wheels, hollow spaces inside each one. Shaft has channels between the cavities of the shaft and the impellers, hollow spaces. Compressor shaft channels are connected to the cooling heat exchanger. Output of the hollow spaces between the turbine impellers and the turbine inlet is connected to the heat exchanger. Heat machine with internal heat recovery can be used in large, average power engineering, individual household appliances, transport equipment and other spheres that require conversion of thermal energy to mechanical energy and vice versa.

EFFECT: technical result: higher efficiency of the thermal machine due to heat recovery within a closed continuous thermodynamic cycle.

1 cl, 2 dwg

Description

The invention relates to engine building and can be used in thermal power plants, automobiles, refrigerators, heat pumps and other processes for converting thermal energy into mechanical energy and vice versa as a “heat pump”.

The known scheme of a closed cycle gas turbine installation, Moiseev G.I., Meerov L.Z. The design of stationary gas turbine units. - M.: Gosenergoizdat, 1962.

The closest to the claimed technical solution in terms of technical nature and the technical result achieved is the Escher Visc Closed Circuit Gas Turbine Unit (p. 94). The described device is taken as a prototype of the invention.

The disadvantages of the prototype:

The heat of the exhaust gas is transferred after expansion in the turbine and after compression in the compressor in the recovery heat exchanger. In this connection, the final temperature of gas heating after the turbine decreases and the initial temperature of gas heating after the compressor increases due to expansion and compression of gas in the impellers. In this connection, the possibility of using heat during its recovery decreases.

An object of the invention is:

1. The expansion of the temperature range during heat recovery during the entire working thermodynamic cycle.

2. Improving the efficiency of the heat engine.

The problem is solved as follows:

The heat recovery heat exchanger of the heat engine is implemented inside the compressor and turbine. Structurally made in the form of alternately mounted impellers and hollow spaces through which heating and heated gases flow in opposite directions. The shaft on which the wheels are mounted has channels through which gases are supplied and discharged.

SUMMARY OF THE INVENTION

In FIG. 1 shows a turbocompressor heat engine operating in a closed thermodynamic cycle with internal heat recovery in longitudinal section and consists of radial compressor 1 and turbine 2. Inside the compressor 1 and turbine 2, movable impellers 6 and hollow spaces 3 are alternately located for the oncoming flow of the gaseous working fluid in relation to the flow in the impellers. The shafts of the blocks have channels 4 and openings 5 for gas passage between the shaft cavities and the impellers 6, hollow spaces 3. The compressor shaft channels 4 are connected to the cooling heat exchanger 8. The output of the hollow spaces 3 between the turbine impellers and the turbine inlet are connected to the heating heat exchanger 9. Heat recovery occurs through the walls of the impellers according to the principle of a regenerative heat exchanger. Heat flows between the gas stream of the hollow space 3 and the gas stream flowing through the impellers 6, while the increase in temperature gradients in the compressor and turbine is directed from the center to the outer circumference of the impellers in radius. When heating the gas passing through the compressor and cooling the gas in the turbine, the process is approximately isochoric; accordingly, work on its compression and expansion is almost not spent.

Due to the closure of the cycle, the kinetic energy of the stream exiting the turbine is not lost and returns back to the cycle.

When the impellers rotate and gas passes through the hollow spaces between the impellers and inside the impellers, the heat transfer coefficients between the flows and the walls of the wheels increase.

In FIG. 2 is a diagram of a thermodynamic cycle taking place in a turbocompressor heat engine operating in a closed thermodynamic cycle with internal heat recovery. The supply of heat Q1 to the cycle is carried out in a heating heat exchanger at the end of the isobar 2-3 at a gas pressure of P2. Heat recovery Qr1 in the turbine is carried out between isochore 3-4 and isobar 2-3. Heat recovery Qr2 in the compressor is carried out between isochore 1-2 and isobar 4-1. Heat removal Q2 from the cycle is carried out in a cooling heat exchanger at the end of isobar 4-1 at a pressure P1.

Claims (1)

A turbocharger heat engine operating in a closed thermodynamic cycle with internal heat recovery consists of a radial compressor and a turbine, movable impellers are located inside each one, hollow spaces, the shaft has channels between the shaft cavities and the impellers, hollow spaces, the compressor shaft channels are connected to cooling heat exchanger, the exit of the hollow spaces between the impellers of the turbine and the turbine inlet are connected to a heating heat exchanger.

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