RU2586236C1 - Internal combustion engine - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: invention relates to power engineering and can be used as an aircraft engine. Internal combustion engine includes tight housing (1) in form of truncated cone partially filled with heat carrier. Housing includes evaporator (2) and capacitor (3). In housing there is a heat-insulation ring (4), which is an element of housing and rigidly fastened with both evaporator and condenser of engine. To heat-insulation ring is rigidly attached impeller (5) of turbine with working blades, encircled by rim (6). Turbine wheel is rigidly secured to hollow shaft (7) of engine. Nozzle is installed on hollow shaft gear (8) of turbine, encircled by a rim (9), which is made up of internal annular magnet. Rims of both wheels are mounted so that annular gap (10) is formed with housing. Wheel with nozzle blades is installed with possibility of rotation relative to hollow shaft - on bearings (11). Above inner annular magnet there is outer annular magnet (12) rigidly connected to housing (13) of aircraft. On hollow motor shaft is rigidly fixed screw (14). In engine housing, in condensation zone, there are heat-conducting rods (15) on which are rigidly fixed plates (16), profile formed by technological operation "rolling" on both sides. Spiral is located around evaporator combustion chamber (17) with nozzles (18). Inside evaporator there is a metallic finely porous sponge (19).

EFFECT: higher engine power, safety of its transportation in idle state, as well as reduced weight and size.

3 cl, 8 dwg

Description

The invention relates to the field of power engineering and can be used, in particular, as the engine of an aircraft (LA).

A device of the engine is known [1], which contains internal and external radiators containing thin-walled plates with a developed heat exchange surface.

The disadvantages of the known device include a relatively low heat exchange surface of radiators, which reduces engine power.

The second disadvantage is the inability to safely transport the engine in an idle state, due to a significant amount of coolant moving freely and randomly in the volume of the sealed engine casing.

The third disadvantage is the relatively high weight and size characteristics of the engine, due to the presence of a solid motor shaft.

The aim of the present invention is to increase the power of the engine, its safe transportation inoperative, as well as the reduction of overall dimensions.

The essence of the invention lies in the fact that to increase the efficiency of heat transfer, the cone plates of the radiators are subjected to the “knurling” operation on both sides, as a result of which the heat transfer surface increases significantly, and numerous protrusions are formed on both surfaces, which facilitate the conversion of crushed steam into condensate.

The invention is illustrated by drawings.

In FIG. 1 shows the appearance of the engine.

In FIG. 2 shows a single-stage turbine.

In FIG. 3 shows a hollow shaft of an engine with conical plates and heat-conducting rods.

In FIG. 4 shows the profile of the cone plate after the knurling operation.

In FIG. Figure 5 presents the motion diagram of the coolant, the motion diagram of atmospheric air, as well as the triangle of the distribution of forces acting on the coolant.

In FIG. 6 shows the surface profile of the cone plate before the knurling operation. Increased.

In FIG. 7 shows the surface profile of the conical surface after the knurling operation.

In FIG. 8 shows profiles of two adjacent conical plates.

The device of an external combustion engine

The external combustion engine contains a sealed housing 1 in the form of a truncated cone, partially filled with coolant. The housing contains an evaporator 2 and a condenser 3. The housing contains a heat-insulating ring 4, which is an element of the housing and is rigidly bonded to both the evaporator and the engine capacitor. The impeller 5 of the turbine with rotor blades enclosed by the rim 6 is rigidly attached to the heat-insulating ring. The impeller of the turbine is rigidly attached to the hollow shaft 7 of the engine. A nozzle wheel 8 of the turbine is installed on the hollow shaft, covered by a rim 9, which is an internal ring magnet. The rims of both wheels are installed with the formation of an annular gap 10 with the housing. A wheel with nozzle vanes is mounted rotatably with respect to the hollow shaft on bearings 11. Above the inner ring magnet, an external ring magnet 12 is mounted rigidly connected to the aircraft body 13. A screw 14 is rigidly fixed to the hollow shaft of the engine. In the engine housing, in the condensation zone, there are heat-conducting rods 15 on which conical plates 16 are rigidly fixed, the profile of which is formed by the knurling operation on both sides. Around the evaporator there is a spiral combustion chamber 17 with nozzles 18. Inside the evaporator there is a metal finely porous sponge 19.

Engine operation

When fuel is supplied to the nozzles 18, as well as compressed air into the 2-spiral combustion chamber 17, heating and evaporation of the coolant in the evaporator 2 occurs. Steam under pressure enters the blades of the nozzle wheel 8. Since the nozzle wheel with guide vanes is locked from rotation by means of internal and external magnets, and the impeller 5 is rigidly connected by means of the hollow shaft 7 to the housing 1, the engine comes into rotation. The coolant in the vapor state, passing through the turbine, enters the condenser 3, where it transfers part of the heat to the external radiator through the heat-conducting rods 15, and passes into the liquid phase - condensate. Having passed into the liquid phase on the inner cone plates, the coolant precipitates on the inner wall of the condenser 3 and returns to the evaporator 2 as a thin film under the action of centrifugal forces. For this purpose, there is a gap 10 between the casing 1 and the rims 9 of the turbine wheels. the heat received from the combustion chamber 17, again passes into a vaporous state and enters the turbine wheels. The cycle closes.

The advantage of the proposed external combustion engine

Any heat engine must contain at least four devices: 1. An energy source. 2. The heat engine. 3. Capacitor. 4. The pump.

Typically, all these devices exist independently, occupy large areas and volume, and are interconnected by a complex communication system. In the proposed technical solution, all the necessary devices are combined in one mobile unit, and the pump itself performs the function of the engine, the casing of which is made in the form of a cone.

1. Having set the required value of the taper of the casing (angle α), the number of revolutions n and the radius R, as well as the size of the gap between the turbine and the casing, it is guaranteed to ensure reliable passage of the heat carrier with opposite directions. Namely: in the gaseous state - from the evaporator to the condenser, passing through the turbine, and vice versa, in the liquid state - from the condenser to the evaporator. Moreover, an aircraft with a similar engine, the operation of which does not depend on spatial orientation, can perform any aerobatics.

2. The dense installation of numerous conical plates with a developed heat transfer surface and the presence of numerous protrusions on the surface, as well as the presence of numerous heat-conducting rods, ensure that crushed steam first goes into saturated steam and then into condensate.

3. The engine is omnivorous, ie undemanding to fuel quality. The nozzle can be configured for any type of fuel, while in liquid or gaseous form.

4. The stationary engine can run on solar energy.

5. The engine can work in the power unit mode (engine - electric generator).

6. An anaerobic version of the engine, in which radioactive fuel elements (fuel elements) in the form of tubes tightly enclose the evaporator body, can be used in underwater position.

7. An anaerobic engine can also be used for space engineering. For example, as a BIP - an on-board power source, instead of solar panels, regardless of the distance from the Sun.

8. The finely porous metal sponge represents several layers of a metal mesh with a mesh size of 100-150 microns [3].

Information sources

1. RF patent No. 2472005 with priority dated January 18, 2011.

2. The article "knurling". Polytechnical dictionary, publishing house "Soviet Encyclopedia", Moscow, 1980, p. 319.

3. Yandex. Wick or capillary structure.

Claims (3)

1. The external combustion engine contains a sealed housing in the form of a truncated cone, partially filled with coolant, the housing contains an evaporator and a condenser, the housing contains a heat-insulating ring, which is an element of the housing and rigidly attached to both the evaporator and the engine condenser, is rigidly fixed to the heat-insulating ring turbine impeller with impellers covered by a rim, turbine impeller is rigidly attached to the hollow shaft of the engine, a nozzle turbine wheel is installed on the hollow shaft, oh With a rim representing an inner ring magnet, the rims of both wheels are mounted to form an annular gap with the housing, the wheel with nozzle vanes is mounted rotatably with respect to the hollow shaft - on bearings, an outer ring magnet is mounted rigidly connected to the housing above the inner ring magnet aircraft (LA), a screw is rigidly fixed to the hollow shaft of the engine, in the engine housing, in the condensation zone, there are heat-conducting rods on which plates, wok are rigidly fixed The evaporator has a spiral combustion chamber with nozzles, characterized in that the plate profile is formed by the knurling operation on both sides of the surface. 2. The engine under item 1, characterized in that the evaporator contains a metal finely porous sponge. 3. The engine according to claim 1, characterized in that the engine shaft is hollow.

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