RU2552532C1 - Electrical machine cooling device - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: electrical machine cooling device comprises a stator with axial cooling channels, Peltier's module, the junctures of which are electrically isolated from the electrical machine structure. Cold junctures of Peltier's module are interfaced to the external surface of the stator package, and hot ones are interfaced to the internal surface of the electrical machine housing. Peltier's module is heat isolated by its 1/5 of the section from hot junctures. Peltier's module is connected by electric terminals to DC power supply - the thermocouple battery, the hot juncture of which is located in the combustion chamber of the aviation engine, and the cold juncture - on the housing of the input part of the aviation engine interfaced to the air inlet.

EFFECT: use of thermal energy of aviation engine for power supply of active cooling system.

4 dwg

Description

The invention relates to thermoelectricity, in particular to electric machines, namely, cooling devices for aircraft engine generators, and relates to the features of the structural design of their cooling system.

The electric machine is known as a synchronous machine with liquid channel cooling (Naumenko V.I., Klochkov. O.G. Aircraft with intensive cooling. M., "Mechanical Engineering", 1977, p. 9). It is equipped with a package of stator plates with radial cooling channels and a rotor package with axial cooling channels.

The disadvantages of this machine are the heating of the cooling agent when it flows through the frontal part of the winding until it enters the active part of the stator and rotor and the absence of active means to reduce the temperature of the stator magnetic circuit and the cooling agent.

An electric machine is known as a synchronous machine with liquid-cooled liquid-jet cooling (Naumenko V.I., Klochkov. O.G. Intensive-cooling aircraft. M., Mashinostroyeniye, 1977, p. 9), in which convective heat exchange with liquid refrigerant is carried out supplied by jets into the internal volume of the machine directly on the surface of the fuel elements.

The disadvantages of this design are the lack of active cooling means and the possibility of ignition of the refrigerant when using, for example, fuel.

The electric machine is known as a synchronous machine with evaporative liquid cooling (Naumenko VI, Klochkov. OG Aircraft machines with intensive cooling. M., "Mechanical Engineering", 1977, p. 12). During evaporative cooling on heat-generating surfaces, heat exchange occurs with a fluidized bed of refrigerant. The boiling process on the surface causes artificial turbolization, which leads to a very high intensity of heat removal. When refrigerant vapors are released overboard, heat is transferred outside the aircraft.

The disadvantages of this machine are:

- the need for the presence on board the aircraft stock of refrigerant, which is an additional load;

- the inability to use fuel as a refrigerant due to the high probability of ignition;

- contamination of refrigerated surfaces with products of refrigerant decomposition;

- lack of active means to reduce the temperature of the fuel parts of the machine.

The listed designs of cooling systems use methods with significant disadvantages in which there are no active cooling elements.

Closest to the claimed is the design of a synchronous electric machine with liquid cavity cooling (Naumenko VI, Klochkov OG Aircraft machines with intensive cooling, M., "Engineering", 1977, p. 10,) which contains an axial stator cooling, divided into several parts with the formation of axial channels.

The disadvantage of this analogy is the lack of a process of actively reducing the temperature of the stator magnetic circuit, including a cooling agent, the temperature of which increases as the elements flow around the windings and the magnetic circuit of the machine.

The objective of the present invention is to create an active cooling system that increases the efficiency of an aircraft electric machine, reducing its weight, with electrical power to this system from a thermoelectric current source that does not increase the weight of on-board equipment, operating on the principle of using a large temperature difference, for example, an engine combustion chamber and its the coldest part, without additional fuel consumption using thermal energy, uselessly dissipated in space.

The technical result is the use of dissipated useless thermal energy of an aircraft engine (auxiliary or sustainer) to power an active cooling system,

The problem is solved, and the technical result is achieved in that the cooling device of an electric machine, including a stator with axial cooling channels, according to the invention contains a Peltier module, the junctions of which are electrically isolated from the structure of the electric machine, the cold junctions of which are interfaced with the outer surface of the stator package, and hot - paired with the inner surface of the body of the electric machine and insulated 1/5 section with the side of the contact bus of the Peltier module, connected a source of electrical current, which is a thermocouple or battery thermocouple hot junction is located in the combustion chamber of an aircraft engine, a cold junction - the housing inlet part of an aircraft engine with an air intake conjugate.

The invention is illustrated by drawings.

In FIG. 1 is a longitudinal section through an electric machine (aircraft engine generator) with an active cooling system.

In FIG. 2 is a structural diagram of a Peltier module for an aircraft engine generator.

In FIG. Figure 3 shows an image of a Peltier module without a thermal insulation layer.

In FIG. Figure 4 shows the power supply circuit of the Peltier module from a battery of thermocouples operating from the temperature difference of parts of an aircraft engine and aircraft.

The aircraft engine generator (Fig. 1) consists of a housing 1, a stator package 2 with a winding 3 pressed into it, a Peltier module 4 installed between them, having a heat-insulating filling of 1/5 section 5 from the side of the hot junctions connected to the housing 1, and cold junctions associated with the package of stator 2 (Fig. 2), electrically isolated from them by a layer of 6 and 7, with electrical leads 8, forming channels 9 for flowing refrigerant, rotor 10 with the housing 1 and individual elements of the Peltier module 4.

The Peltier module without thermal insulation filling shown in FIG. 3, has four sectors 11, each of which consists of batteries of p- and n-cells 12 and 13, electrically connected in series by buses 14 and 15. Between the sectors channels 16 are formed for power ribs 17 coordinating and holding the stator package 2.

A generator with an active cooling system operates as follows.

The generator drive on board the aircraft is carried out from aircraft (auxiliary or marching) engines. When the rotor 10 rotates, its magnetic field excites an EMF in the stator winding 3, under the influence of which a load current flows through its circuit, which causes losses and heating of the machine as a whole. To ensure thermal conditions, the generator is cooled by pumping refrigerant through channels 9 formed by the housing 1, the stator package 2 and the elements of the Peltier module 4. The Peltier module 4 is connected by electrical leads 8 to a constant current source - thermocouple battery 18 (Fig. 4), whose hot junction 19 is located in the combustion chamber of the aircraft engine 20, and the cold junction 21 is on the body of the inlet part of the aircraft engine 22, coupled with the air intake. Under the influence of the flowing current on the module, some junctions are cooled, others are heated (cold and hot junctions (Fig. 1)). Cold and hot junctions are electrically isolated from the structural elements of the electric machine (Fig. 2). The outer surface of the stator package 2 is cooled by cold junctions associated with it, hot junctions are associated with the housing 1, cooled by external blowing. The refrigerant pumped through channels 9 is cooled by elements of the Peltier module 4 forming these channels 9.

Thus, the inventive method allows to increase the efficiency of an electric machine, reduce its weight, eliminate the risk of ignition of the refrigerant and contamination of the cooled surfaces.

Claims (1)

A cooling device of an electric machine, including a stator with axial cooling channels, characterized in that it contains a Peltier module, the junctions of which are electrically isolated from the structure of the electric machine, the cold junctions being coupled to the outer surface of the stator package, and the hot junctions being connected to the inner surface of the body of the electric machine and insulated 1/5 section from the side of the contact bus of the Peltier module, connected to an electric current source, which is a thermocouple or a thermocouple battery p, the hot junction of which is located in the combustion chamber of the aircraft engine, and the cold junction is on the housing of the inlet part of the aircraft engine, coupled with the air intake.

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