Device for ice removal from gas turbine air intake |
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IPC classes for russian patent Device for ice removal from gas turbine air intake (RU 2481480):
 Set of containers for steamed cooking in microwave oven / 2432893
Invention relates to cooking. Set of containers is designed for steamed cooking food in a microwave oven and contains the water tank, food container with lots of holes in its bottom, which includes inner and outer parts of wall, as well as material shielding from microwave radiation enclosed between the inner and outer parts of the walls. Also, the device contains a cover containing the inner and outer parts, as well as material shielding from microwave radiation enclosed between the inner and outer parts of the walls of the cover. At that the food container is made to be mounted or dismounted inside the water tank. When the set is assembled, the cooking food is shielded from direct exposure of microwave energy.
 Method for manufacturing of multi-chamber pack with permeable wall between chambers, suitable for use in microwave oven / 2401224
Application describes method for manufacturing of multi-chamber pack with internal one or several open or closed chambers, suitable for use in microwave oven, as well as multi-chamber pack. Invention provides for the following: multi-chamber pack having inner permeable wall between chambers is made from single sheet of flexible packing film. The first chamber may contain food product, and the second chamber - source of steam.
 Microwave oven to produce ceramic pigments, method of furnace application / 2361374
Invention relates to electric engineering and, particularly, to microwave ovens designed to treat and produce ceramic pigments. The microwave oven contains multi-mode cylindrical chamber (10), one or more diametrically opposite to each other electro-magnetic wave generators (16) located along the inner surface of the said chamber and pipe (11) made from microwave-transparent or low absorbing material. The said pipe is inside the above-mentioned chamber. The pipe is open from both end sides (12), which project from the chamber, and equipped with rotary disc (13). The said rotary disc is implemented as a one-piece element together with pipe (11) and coupled with related actuation unit (14).
 Microwave resonator for thermal processing of materials, device for thermal processing of materials, method for operation of microwave resonator and thermally processed product / 2312470
Device is the multi-vertex resonator with even number of vertexes, wherein highest mode of microwave is generated and, thus, large space is created in resonator cavity, characterized by homogeneous field distribution for even thermal processing of half-finished materials. Along at least one joint edge of side surface segment, input structural couple is mounted outside, consisting of at least one rectangular hollow wave duct positioned to the left and right from it for injection of main mode microwave. Common part of wall of rectangular hollow wave duct and resonator contains input structure positioned longitudinally to it, consisting of serially positioned apertures in resonator wall. Technological line may be assembled using such microwave resonators in form of modules, in which line various thermal processes may be conducted, such as heating, exposure at certain temperature and controlled cooling. For precise adjustment of field evenness, input structural pairs are used when preserving given power of radiation in resonator and in case of contra-directional deviations in radiation of specific power.
 Device and method for destroying insects and fungi, destroying wood, and for processing materials, containing harmful substances / 2296438
In accordance to inventions, two magnetrons G1, G2 or antennas only are mounted on object being irradiated O, directly in front of each other. Method of temporary alternation of generators control is available in device. By means of signals from thermo-measuring probes, processed by computer, and by means of signals formatting block, control device and generators G1, G2, operation mode of generators G1, G2 is precisely set to precise temperature required for object O, including temperature mode. Usage of microwaves for processing objects and items, infected with pests and/or containing harmful substances, allows achievement of controlled increase of temperature and therefore of destruction of harmful organisms and decontamination of these objects.
 Microwave oven with coffee maker and its control method / 2287915
Microwave oven with coffee maker includes: housing; food cooking chamber arranged in housing; compartment formed in housing and designed for placing different electric components on its inner surface; container arranged at one side of said compartment and designed for placing in it vessel for water, heating member, funnel, water supply tube and tubular member for feeding water at coffee extraction. Container prevents heat transfer from heating member to said compartment.
 Coffee maker and microwave oven provided with the coffee maker / 2280400
Coffee maker prevents water leakage when emptying container for water storage. Microwave oven provided with such a coffee maker is also described. Coffee maker has container for water which container keeps water intended for extracting coffee. Container has outlet hole made in one of side walls, tube which guides water withdrawn through outlet hole of container for keeping water to perform extraction of coffee, and connecting unit. The latter has first connecting member with one end to be connected with container for keeping water. Second connecting member of connecting unit has one end connected with tube and its second end is dismountable connected with first connecting member. Connecting unit connect container for water with tube and prevents leakage of water from at least one container of water or tube when first connecting member is disconnected from the second one.
 Microwave heater for fluid or free-flowing substances / 2264052
Device has electromagnetic energy emitter, positioned in radio-transparent pipe, positioned in reservoir with processed substance. Electromagnetic energy emitter is in form of two-conductor line and consists of two conductors - first and second ones. One of these due to its configuration has greater length, than another one, i.e. made extended. This extension can be either monotonous along whole line axis, or provided by phase-shift elements, included in conductor with certain step. To input of two-wire line UHF energy is fed from symmetric output of UHF energy source.
 Installation and method for production of nanodispersed powders in microwave plasma / 2252817
The installation comprises production-linked: microwave oscillator 1, microwave plasmatron 2, gas-flow former 3, discharge chamber 4, microwave radiation absorber 5, reaction chamber 6, heat-exchanger 7, filter-collector of target product (powder) 8, device for injection of the source reagents in a powdered or vapors state into the reaction chamber, the installation has in addition a device for injection of the source reagents in the liquid-drop state, it has interconnected proportioner 9 in the form of cylinder 10, piston 11 with gear-screwed electric drive mechanism 12 adjusting the speed of motion of piston 1, evaporative chamber 13 with a temperature-controlled body for regulating the temperature inside the chamber that is coupled to the assembly of injection of reagents 14 in the vaporous state and to the assembly of injection of reagents 15 in the liquid-drop state, injection assembly 14 is made with 6 to 12 holes opening in the space of the reaction chamber at an angle of 45 to 60 deg to the axis of the chamber consisting at least of two sections, the first of which is connected by upper flange 16 to the assemblies of injection of reagents, to discharge chamber 4, plasmatron 2, with valve 17 installed between it and microwave oscillator 1, and by lower flange 18, through the subsequent sections, it is connected to heat exchanger 7, the reaction chamber has inner water-cooled insert 20 rotated by electric motor 19 and metal scraper 21 located along it for cutting the precipitations of powder of the target product formed on the walls of the reaction chamber, and heat exchanger 7 is made two water-cooled coaxial cylinders 22 and 23, whose axes are perpendicular to the axis of the reaction chamber and installed with a clearance for passage of the cooled flow, and knife 24 located in the clearance, rotating about the axis of the cylinders and cleaning the working surfaces of the cylinders of the overgrowing with powder, powder filter-collector 8 having inside it filtering hose 25 of chemically and thermally stable material, on which precipitation of powder of the target product from the gas flow takes place, in the upper part it is connected by flange 26 to the heat exchanger, and in the lower part the filter is provided it device 27 for periodic cleaning of the material by its deformation, and device 28 with valve 29 for sealing the inner space of the filter. The method for production of nanodispersed powders in microwave plasma with the use of the claimed installation consists in injection of the source reagents in the flow of plasma-forming gas of the reaction chamber, plasmochemical synthesis of reagents, cooling of the target product and its separation from the reaction chamber through the filter-collector, the source reagents are injected into the flow of plasma-forming gas, having a medium-mass temperature of 1200 to 3200 K in any state of aggregation: vaporous, powdered, liquid-drop or in any combination of them, reagents in the powdered state are injected in the form of aerosol with the gas-carrier into the reaction chamber through injection assembly 35 with a hole opening into the space of the reaction chamber at an angle of 45 to 60 deg to the chamber axis, reagents in the liquid-drop or vaporous state are injected into the reaction chamber through injection assemblies 15 or 14, respectively, in the form of ring-shaped headers, the last of which is made with 6 to 12 holes opening into the space of the reaction chamber at an angle of 45 to 60 deg to the chamber axis, each of them is blown off by the accompanying gas flow through the coaxial ducts around the holes, at expenditure of the source reagents, plasma-forming gas, specific power of microwave radiation, length of the reaction zone providing for production of a composite system and individual substances with preset properties, chemical, phase composition and dispersity.
 Microwave oven with built-in percolator / 2250574
Novelty is that percolator is installed in electronic device chamber. Resonator is closed at front with door. Electronic device chamber accommodating electrical pieces of equipment is disposed near resonator. Percolator housing is disposed in front of electronic device. Water tank is made inside housing. Funnel is free to be brought in and taken out of housing interior. Container is made in the form of jug or cup. Heater is installed in bottom part of housing. Water supply pipe is connected on one end with water tank, pipe body is partially passed through bottom part of housing to bring it in contact with heater, and other end of pipe is disposed on upper part of funnel.
 Air intake for aircraft nacelle / 2480598
Air intake installed upstream of a middle element of the nacelle of the aircraft engine includes the following: an external wall with an end face, front partition wall (108), supply mechanism (105), and supply pipe (107). Front partition wall (108) together with the external wall restricts anti-icing compartment (103) in the end face. A hole is made in the partition wall. Supply mechanism (105) provides hot air supply to anti-icing compartment (103). Mechanism (105) includes supply pipe (107) for hot air supply and peripheral sealing element (109) enclosing the above supply pipe (107). Supply pipe (107) has bent free end (111). Hole (113) in the front partition wall is made so that free end (111) passes through it along main axis (115) of the supply pipe. Sealing element (109) includes contact plate (121) enclosing the above pipe (107) so that tightness is provided in the zone of front partition wall (108).
 Coating for acoustic treatment including function for hot air processing of ice crust / 2471680
Coating is designed for acoustic treatment at the level of airborne vehicle surface. The coating contains acoustically resistive layer (28), cellular structure (30) and reflecting layer (32). Between cellular structure and acoustically resistive structure, channels (34) are located, each one of which is bounded by wall (36) other than walls of cellular structure, and one of channel ends is connected with hot air inlet.
 Coating for acoustic treatment, front edge and air intake of aircraft, comprising such coating / 2468226
Coating for acoustic treatment applied on the front edge of an air intake of an aircraft gondola, comprises an acoustically resistive layer, a cellular structure and a reflecting layer. The cellular structure comprises many channels, exiting at one side at the level of the first surface and at the other side - at the level of the second surface. The cellular structure comprises cuts or holes arranged at the level of side walls of several channels, making it possible to establish communication between adjacent channels so that a network of communicating channels is established to isolate one or a group of non-communicating channels. At least one of communicating channels is connected with a hot gas input. The other inventions of the group relates to a front edge of an aircraft and an air intake of an aircraft gondola, comprising the above coating for acoustic treatment.
 Heat-transfer system for gas turbine engine / 2449143
Heat-transfer system for a gas turbine engine with an air intake fairing comprises a circular jacket of a fan, a circular airing of an air intake arranged in front of the circular jacket of the fan, a heat exchanger having a source of heat passing through it and installed outside the circular jacket of the fan; and multiple heat tubes, every of which passes between the heat exchanger and the inner space of the air intake fairing. Each heat tube comprises a rear section passing in axial direction, a transition section passing in circular direction and having an arched shape. The transition section connects the rear section and the front section with each other arranged near the top of the air intake fairing. The front section passes inside the air intake fairing, at the same time front sections of each heat tube are arranged inside the air intake fairing along the circumference.
 Heat transfer system / 2447300
Heat transfer system for gas turbine engine comprising annulus casing to accommodate several post elements extending, in fact, radially, includes, at least, one arc-shaped heat tube. Heat tube stay in contact with housing outer surface and communicates with heat source to allow heat to be transferred via heat tube and housing to post elements.
 Anti-ice system of aircraft gas turbine engine inlet cone / 2444638
Anti-ice system 2 on aircraft gas turbine engine inlet cone 4 comprises air diffuser 18 arranged in engine inlet cone to feed hot air therein. Said system comprises also circuit 20 to remove supercharged air from constricted cavity of turbine engine. Said circuit communicates with diffuser to supply hot air therein. Aircraft turbine engine incorporates above described anti-ice system. Proposed method of de-icing features the use of above described system.
 Air-cleaning device for gas-turbine plant / 2440502
Air-cleaning device for gas turbine plant includes air receiving chamber, air filters located in tiers in air receiving chamber, heating system of cycle air with loop pipeline supplying the hot air to air receiving chamber, and connecting pipeline. Tubular elements from heat-conducting material are passed through walls of exhaust line of gas turbine plant across the line. On one side the tubular elements are interconnected with atmosphere, and on the other side they are connected to the header that in its turn is connected to loop pipeline. Tubular elements are preferably equipped with common air intake at the inlet of which a fan is installed.
 Gas turbine engine with aft fan / 2439347
Proposed engine comprises gas generator arranged at compressor inlet, compressor shell fairing connected by inlet posts with air intake and, further, with engine nacelle. Compressor shell fairing and air intake have annular slotted spaces with airflow about. Heated rotary inlet distributor is arranged between said posts and compressor rotor. Distributor vane inner cavities communicate at inlet via vane outer pins with compressor intermediate stage and, at outlet, with fairing slotted annular space of compressor shell communicated via hollow inlet posts with air intake slotted space communicated with atmosphere at outlet.
 Air cleaning device for gas turbine plant / 2439346
Air cleaning device for gas turbine plant includes air receiving chamber (1), air filters (2) located in tiers in air receiving chamber, heating system of cyclic air with ring pipeline (3) supplying hot air to air receiving chamber, and connecting pipelines (7). As heating source of cyclic air there used is section of exhaust path of gas turbine engine. This section of the path is enclosed in heat insulating casing (5) with formation of heat accumulating capacity (6) that is interconnected on one side with atmosphere and on the other side with ring pipeline. Fan (8) is preferably installed at the inlet of heat-accumulating capacity.
 Air-cleaning device of gas-turbine drive / 2436976
Air-cleaning device of gas-turbine drive consists of air receiving chamber with filter elements arranged in it and sediment retaining surfaces before inlet orifices formed on it, and of gas ducts of system of cycle air heating. Sediment retaining surfaces are made on the air receiving chamber before inlet orifices. Sediment retaining surfaces are made in form of sheets perforated with cells of laminar type. Sediment retaining sheets are preferably made of plastic materials. Dimensions of the device are decreased due to design of sediment retaining surfaces made of sheets perforated with orifices of laminar type. Additionally, air penetrability of sediment retaining sheets reduces windage of the structure and reduced dimensions decrease snow load and metal input of the structure.
 Device to detect and remove ice or fluid layer / 2453475
Proposed device comprises, at least, two subnets 2a, 2b of conducting elements. Every said subnet comprises, at least, one line of elements 3. Subnets are arranged so that finger joint between first subnet conducting element 3 and second subnet conducting elements 3 make network of capacitance pickups. Said conducting elements double as heating elements designed to eliminate icing. Conducting elements are buried in insulation material 4. Every subnet of conducting elements is integrated in flexible backing 5, 5a, 5b. The complex proper makes flexible coating. Aircraft comprises above described device connected to crew cab instrumentation panel via switch to display operating parameters and to control said device.
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FIELD: engines and pumps. SUBSTANCE: device (50) for ice removal from air intake (24) of gas turbine (10) includes metal cover (52) for air intake (24) of the gas turbine. The cover includes the first air inlet opening (54) to cover (24), which is equipped with the first metal grid (56). The cover includes the second opening (58) intended for air direction to compressor stage (20) of the gas turbine. Device includes means (62, 64) for generation to the cover of electromagnetic waves having the frequency allowing to melt the ice. The helicopter turbine engine is characterised by use of the air intake ice removal device. EFFECT: reduction of ice removal power consumption. 10 cl, 1 dwg
The present invention relates to the field of aviation and industrial internal combustion engines, and in particular, but not exclusively, to a gas turbine aircraft, such as turbine engines, which are equipped helicopters. It relates in particular to internal combustion engines such as gas turbines, which contain the inlet and which are designed for operation in conditions, when the air vent can be formed ice, in particular on the protective screen placed in the above-mentioned intake and designed to prevent extraneous objects to get into the engine. It is well known that due to specific meteorological conditions at the inlet of the gas turbine can be formed ice in such a quantity that can lead to the partial overlap between the intake of a gas turbine, which may cause a complete or partial damage of the gas turbine. In the case of helicopters this phenomenon of icing can occur in particular when the helicopter moves in the wet and cold atmosphere, for example in the mountains or near the water. It is easy to understand that there is a risk of icing is forcing the aircraft to stay on the ground to eliminate any possibility of power loss, and what about the engine stops in flight. The present invention relates, therefore, to a device for removing ice from the air intake of the internal combustion engine, such as gas turbine, installed, for example, in a turbine engine helicopter. Among the known devices for removing ice, you can mark those that use air under pressure is taken at the output of the compressor stage of a gas turbine in order to melt the ice. In these devices, the air under pressure supplied from the output of the compressor stage to the inlet for heating zones of the engine, prone to icing, such as, for example, stationary parts, like nozzle air intake of the engine or moving parts such as the blade pre-twist thread, usually equipped with swivels, placed directly at the input of the compressor wheel. The main disadvantage of these devices is that they are very energy-intensive, as they take a significant amount of energy necessary for thermodynamic cycle of this engine, gas turbine, greatly compromising the overall efficiency of the engine, and the maximum level backup engine power. This type of energy extraction is also ineffective, since the operation of the heating leads to subsequent undesirable cooling when the extension of the AI air in the area. When the engine is a gas turbine, another disadvantage is that the ice removal is not possible, when the gas turbine is running at idle, the compressor is not supplying enough air, pressure, temperature and flow rate which would remove the ice. In this case, it is clear that the operation of removing ice is ineffective in the preparatory phases of the approach to landing and landing phase. The aim of the present invention is a device for removing ice, eliminating the above mentioned disadvantages, which is low and which is able to work even when the turbine is running at idle or stopped. The purpose of the invention is achieved in that the device for removing ice according to the invention contains, essentially, a metal shell for the air intake of the engine, with said shell contains the first hole for the entrance of air into the shell, and referred to the first opening provided with a first, essentially, metal bars, the shell contains, in addition, a second opening designed to direct air to the engine inlet, the said device comprises, moreover, means for generating in the shell of electromagnetic waves, the frequency of which helps to ensure the melting of the ice. Preferably the engine is a gas turbine, and the engine inlet is formed by the input of the compressor stage of a gas turbine. In accordance with the invention, the generated waves are directed into the shell to melt the ice contained in the shell or on the first grating, causing vibrations of water molecules that form, resulting in increased temperature of the ice and its subsequent melting. In addition, ice, nemirschi at first, essentially, a metal grate, also heats up the most, essentially, metal bars, the temperature of which is increased due to the interaction of electromagnetic waves, essentially, with the metal material of the first array. By "being metal" in the framework of the invention mean that the item, in particular the shell or first grating may be made of an insulating material such as a composite material containing a surface coating on the base metal. Details, i.e. the shell and lattice, can be done anywhere, metal material nature or essentially of metal. Such details allow, it is preferable to reduce the weight of the device while increasing the efficiency of the device. Indeed, depending on one or more materials forming the surface treatment can be determined on the walls of the shell or at ENISA least on the first reflecting grating zone, absorbing zones, partially absorbing and partially reflecting, depending on the effect you wish to obtain. Use absorbent material allows you to create a warm wall due to the absorption of electromagnetic energy and, on the contrary material that reflects electromagnetic energy, such as gold, allows you to create a cold wall. You can also choose the material, allowing both the absorption of the waves and the spread of inducirowannoe current. The last property of the material provides a special advantage of the increase of the wall temperature, which is able to form ice, in order to prevent its formation. It follows that ice can melt due to the heat effect caused by the absorption of electromagnetic wave absorbing material and/or excitation of the water molecules of the ice due to electromagnetic waves, these waves are reflected reflective walls and/or are receiveaudio waves. Thanks to the present invention, preferably, it is possible not to carry out heating of the blade pre-twist thread, thanks to which it is no longer necessary in a special device for removing ice from these blades; this can simplify the design of the engine. Before occhialino, wave frequency essentially equal to the resonance frequency of water molecules. Electromagnetic waves, preferably, are microwaves. As the microwave frequency is essentially equal to the resonance of water molecules, water molecules, forming ice, vibrate, entering in resonance, so that they absorb a significant amount of energy transmitted by microwaves, so that their temperature increases, at least up to the temperature of their melting, melting, thus the ice. Thanks to the invention of the ice melting is carried out without heating the volume of air entering the intake. Preferably, the frequency of the generated waves, essentially, equal to 2.45 GHz. Thus, provide significant energy savings compared with the device of the prior art, in which air under pressure heats the air stream that is included in the gas turbine. In addition, essentially the first metal lattice forms, preferably, melt the ice electromagnetic screen, filtering the air passing the intake. Thus, microwave, very preferably, allow to melt the ice which may form on the first, essentially, a metal grate. Thus, the first, essentially, metal grill, preferably reflects a part of the electromagnet is s waves, forming, thus, electromagnetic radiation, enclosed in the shell. In other words, ice, nemirschi on the surface of the first grating, will be heated as by using heat from electric currents, which are distributed over the surface of the rods, forming a grid cell, and the wave energy absorbed by the grating in the grating material, and the wave energy of the radiation of each of the bars and also the wave energy emitted from the holes of the lattice. In this embodiment, the space bounded between the first grating and the entrance to the engine, preferably, the input of the compressor stage of a gas turbine, forms a closed area, which is subject to the microwave. Preferably, but not necessarily, means for generating microwaves contain, in addition, wave mixer. Anyway, you can do without, while the wave function of the mixer is provided with movable elements of the compressor stage of a gas turbine in which electromagnetic waves are evenly distributed in the shell. In accordance with another preferred option without wave mixer to concentrate electromagnetic waves in one or more zones, which, preferably, should be freed from the ice. Preferably, the means for gene is investing microwaves contain, at least, magnetron, klystron, or any type of device that can provide this function, while the latter is connected with the casing through a waveguide, which is opened, preferably, the shell of a single output. In accordance with a preferred variant of the waveguide has a ring form for distribution around the circumference of the microwaves in the shell having an annular shape. Preferably, one end of the waveguide contains, in addition, plate, preferably, non-magnetic, permeable to microwaves, designed to ensure that foreign objects do not fall into the waveguide to the magnetron and did not violate its operation. In accordance with a particularly preferred variant of the second hole provided with a second, essentially, a metal grid, which, preferably, provides electromagnetic shielding compressor stage of the engine, performing a second filtering of the air entering the engine. In this embodiment, the space bounded between the first and second, essentially, metal bars, forms, preferably, a closed area, which can propagate microwaves. Preferably, but not exclusively, the second grating has a shape which allows it koltseobrazno be placed around the axis compress the nuclear biological chemical (NBC-speed engine. Preferably, the casing forms a chamber is under pressure. In the framework of the invention under the camera overpressure should be understood casing, the outer walls of which are U-shaped, while the casing has a radial air intake, designed for ring placement around the shaft of the compressor stage. This is especially interesting in the case when the air intake of the engine is circular, while the chamber is under pressure allows, therefore, to control the flow of air axially of the incoming compressor stage. In this embodiment, the chamber is under pressure forms a portion of the area enclosed space for microwaves. In accordance with another preferred due to the low intensity option, the shell formed of the first and second gratings, which are connected to one another by their respective edges, while the shell is limited to the mentioned bars adjacent their respective edges. The present invention relates to a turbine engine helicopter, which contains the air intake includes a device for removing ice according to the invention. Preferably, the device for removing ice according to the invention is placed at the entrance to the compressor stage of the turbine engine. The invention is further explained issleduyuschimi description non-restrictive, with reference to the drawing, showing in section of the turbine engine helicopter, the inlet of which is provided with a device for removing ice according to the present invention. As mentioned above, the present invention can be used in any type of internal combustion engines, in particular gas turbines, which are equipped with turbine aircraft engines and industrial engines. 1 shows in partial section of an internal combustion engine, formed by the turbine engine 10 of a helicopter containing the gas generator 12 and the free turbine 14. The gas generator 12 includes a shaft 16, on which the wheel set 18 centrifugal compressor, housed in a compressor stage 20, while the said shaft 16 also includes a turbine wheel 22. However, it is known that the turbine engine includes an inlet 24 through which the fresh incoming air flows to the compressor stage 20. Compressed air is then routed to the camera 26 of the combustion. The inlet 24 of the turbine engine contains several ducts 28, on each of which an incoming stream of fresh air is suitable radial to axial inlet in the compressor stage. The turbine engine 10 shown on this drawing is supplied by the device 50 DL is the removal of ice according to the present invention, which allows you to remove the ice from the inlet 24 of the turbine engine. In accordance with the invention, the device 50 for removing ice contains, essentially, a metal sheath 52 of the air intake to supply air into the inlet duct 28 of the turbine engine 10. Preferably, the shell still attached to the crankcase 30 of the helicopter. In this case, the shell forms a chamber 52 of excess pressure, the axis of which essentially coincides with the axis of the shaft 16 of the gas generator 12, and which has a height at least equal to the axial length of the duct 28. The camera 52 overpressure contains radially elongated portion, the end of which forms a first radial bore 54 opening to the outside of the turbine engine 10, and through which fresh air enters the device 50 for removing ice. As can be seen from the drawing, the first hole 54 is preferably provided with a first, essentially metal bars 56, allowing, in particular, to filter the air coming into the casing 52. The shell 52 includes, in addition, the second hole 58, intended for the direction of fresh air in the compression stage 20 through the duct 28, while the second hole 58 is made koltseobrazno in the space around the axis of the shaft 16 of the gas generator 12. In the preferred embodiment depicted in Fig. 1, the second is twistie 58 provided with a second, essentially, metal bars 60, which is also annular. As will be explained below, the device 50 for removing ice according to the invention can operate in the absence of the second grating 60. To improve, in addition, security turbine engine 10 can be provided also to the grid 56 and 60 in the axial plane of the slice had the shape of a mushroom cap, through which the air can flow through the axial edge of each of the gratings, despite icing their edges in case of a fault wave generator. In accordance with the invention, the device 50 for removing ice contains, in addition, means 62 for generating microwaves, essentially, a metal shell 52 and, in particular, in space And between the first and second essentially metallic shells. These tools contain mainly the magnetron 62 connected to the waveguide 64. In accordance with the invention the frequency of the generated microwaves, essentially equal to the resonance frequency of water molecules, i.e. approximately 2.45 GHz. Thus, this space And forms a zone that is closed to microwaves, that is, they may be reflected from the boundaries of space A. When the turbine engine is adjudged to be in icing conditions, the ice tends to form in the area A. it has been found that more ice obrazets is on the first grating 56, and to a lesser extent on the second grating 60. In accordance with the present invention, the microwave generated in the space And excite water molecules, forming ice, which are in resonance, resulting in a heating to a temperature exceeding the melting point, whereupon it features ice. In addition, since the first and second grating 56, 60 are essentially metal, microwaves cause different interactions of electromagnetic waves in cells of lattices, in particular radiation, which redirects the waves on the ice. In addition, interaction of electromagnetic waves in the cell array and/or the material of the above-mentioned lattice, such as the absorption of electromagnetic energy and/or the appearance of induced currents circulating in the cells of the grids 56, 60, increase the temperature of the cells and, therefore, substantially prevent the formation of ice on the first and second gratings 56, 60, or cause to melt the ice on these cells. The main invention is that there is no need to heat the entire volume of air that enters the space And or even the entire surface, which adjoins the volume of air that would require significantly more energy than the energy that is radiated by the magnetron 62 in the present invention. Indeed, the magician is etron is the energy source of low entropy, comparable with compressed air output from the compressor stage. Another advantage of the present invention is the use of grids, the cells are made smaller than the cells traditionally used gratings, which enables to improve the filtering of the incoming air. Indeed, it was previously impossible to use cell small size due to an increased risk of rupture of the ice lattice, and this gap would occur the faster, the smaller the cell size. Thus, through the present invention it is possible to remove the ice from the inlet 24 of the turbine engine 12 even when the latter is stopped or running at idle, although the devices of the prior art the removal of ice when installing manually. Additionally it is preferable to use a bit antenna (not shown in the drawing) for protection of compressor speed from the eventual emergence of a plasma in case of malfunction of the device for removing ice. Indeed, in some cases, the compressor blade may behave as an antenna, between the base and the top of which may be an electric field, causing the ionization of the air and the appearance of plasma that can cause damage to the edge portion of the blade. In accordance with a preference for the equipment option work bit antenna is provided by the temperature sensor, which serves to measure the temperature of the volume of incoming air. In accordance with a preferred variant of the device 50 for removing ice contains, in addition, the control system of the magnetron 62, which provides its power consumption depending on the need of the removal of ice. In accordance with another embodiment of the device for removing ice does not contain the second, essentially, of a metal grid. In this case, a closed area for microwaves is limited between the first essentially metal bars 56 and the turbine wheel 18, or any other element located in the compressor stage 20, is able to play the role of the electromagnetic circuit. However, the turbine engine 10 includes, in addition, the blades 70, 72 pre-swirl flow, placed at the inlet of the compressor wheel 18 at the output end of the duct 28. Known, these blade pre-twist of the thread is allowed to Orient the air flow, which is the compressor wheel 18. In accordance with a preferred aspect of the invention the blade pre-twist thread and swivel made of a material mainly permeable to electromagnetic waves, in order to increase the volume and the surface exposed MICR is N. In the invention under "mainly permeable understand that the mentioned item, in particular the blade pre-twist thread and swivel, can be made of a material permeable to microwaves, such as a composite comprising a reflective metal part in the form of a coating on the base metal. An advantage of the present invention is to remove the ice from the blade pre-twist thread without using a special device for defrosting through internal ventilation, such as those usually used in some turbine engines. Thanks to the present invention may, preferably, to simplify the structure of the compressor stage of the turbine engine and to prevent the formation of ice. 1. The device (50) for removing ice from the air intake of the internal combustion engine such as a gas turbine, which is equipped with a turbine engine helicopter, characterized in that it comprises, essentially, a metal shell air intake of the engine that contains the first hole for the entrance of air into the shell, the first hole is provided with a first, essentially, metal bars, and the shell further comprises a second opening that is designed to direct air to the engine inlet, moreover, the device further comprises means for generating in the shell of electromagnetic waves with a frequency to ensure the melting of ice, and a second hole provided with a second, essentially, metal bars, and the first and second gratings form an electromagnetic shield for the removal of ice. 2. Device for removing ice according to claim 1, characterized in that the wave frequency is essentially equal to the resonance frequency of water molecules. 3. Device for removing ice according to claim 1 or 2, characterized in that the means for generating waves contain the magnetron. 4. Device for removing ice according to one of claims 1 to 3, characterized in that the said means also include a waveguide connecting means to generate waves in the shell. 5. Device for removing ice according to claim 1, characterized in that the shell, the first grating and/or the second lattice is made from a material coated with a layer of essentially metallic material. 6. Device for removing ice according to claim 1, characterized in that the casing forms a chamber is under pressure. 7. Device for removing ice according to claim 1, characterized in that the shell forms a closed area for electromagnetic waves. 8. Device for removing ice according to claim 1, characterized in that it contains at least one bit of the antenna. 9. Turbine engine helicopter, equipped with inlet, characterized in that it contains a device for removing ice on demo one of claims 1 to 8. 10. Turbine engine helicopter according to claim 9, characterized in that it further comprises a blade pre-twist thread, located at the entrance of the compressor wheel, and the blades are made of a material which is essentially permeable to electromagnetic waves.
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