BG110826A - GASTERWORK ENGINE - Google Patents

Abstract

The invention relates to a gas turbine engine which is used in mechanical engineering and in particular in small-sized engines for vehicles and for generating electricity. The gas turbine engine includes a compressor and turbine mounted on a connecting shaft, as well as a combustion chamber. According to the invention, the compressor (1) and the turbine (2) are connected to each other by means of a connecting shaft designed as a hollow shaft (3), enclosing the combustion chamber (5) as an outer wall. The compressor (1) and the turbine (2) are mounted on a fixed axis (4) located centrally along the axis of symmetry of the engine. The compressor (1), the turbine (2) and the hollow connecting shaft (3) form the rotor of the motor. The guide device (1.3) and the diffuser (1.4) of the compressor (1), as well as the guide device (2.3) of the turbine (2), are fixed to the fixed axis (4). In embodiments, after the turbine (2), a second turbine (2.4) is mounted to the shaft (4), in the rear part of which a gear ring (2.5) is formed, engaged with a gear (11.1) of the transmission shaft (11). to transmit energy to the consumer. It is possible that the compressor (1) is two-rotor, consisting of an inner (1.1) and outer rotor (1.2), as well as the turbine (2) - respectively of the inner (2.1) and outer rotor (2.2), driven in opposite directions by gear (12) located between them.

Description

FIELD OF APPLICATION

The invention finds application in mechanical engineering, and in particular in the design and construction of small-sized engines for vehicles and the generation of electricity.

BACKGROUND OF THE INVENTION

A compressor is known, a centrifugal type in which the blades are replaced by thin parallel disks. These disks are assembled in a package and spaced approximately equal to twice the thickness of the surface layer (by Ludwig Prandtl) of the respective fluid - gas or liquid. In the center of the disks there is an opening in which the fluid enters. As the disc package rotates, the fluid between the disks experiences the following forces: the adhesion to the disks, the inertial force that resists rotation, and the centrifugal force generated by the rotation of the fluid entrained by the disks. Centrifugal force causes the fluid to be pushed to the periphery of the disk, and adhesion transfers the work of the disks to the fluid. By moving axially into the central opening of the disks, the fluid is trapped in the interstitial space due to the known vacuum created there. Then, the fluid is gradually accelerated, and, describing the spiral trajectory of motion between the disks, is ejected tangentially into their periphery, whereby the fluids are discharged. · · · · · · · · · · Its speed is increasing. From there, it enters the diffuser and is subsequently fed to the high pressure user. The operation of the compressor is based on two known properties of fluids adhesion and viscosity. Adhesion causes the fluid to adhere to a smooth surface, and viscosity impedes fluid separation. causes the entraining of adjacent fluid particles by moving. / 1 /.

A radial-axis compressor known to be based on the Giovanni Branca turbine (17th century) is known, except that it is multi-stage. It consists of two sets of coaxial cylindrical rings, rotating in opposite directions to each other, about a common axis. Its blades have an aerodynamic profile and are cut into the middle of the cylindrical rings. In the end, the cylindrical rings of one set fit almost snugly against the same ones in the other set, with the clearance (clearance) between them dictated by the condition of no friction between them. At the same time, the contact is sufficiently tight to prevent the fluid flowing through it. As they rotate, the blades convert the torque of the shaft into high pressure of the fluid, in which they repeatedly strike the latter and give it energy. Its action is similar to traditional axial compressors, but the direction of its blades is not radial but axial. / 2 /.

There is a known turbine consisting of a set of thin parallel disks as well as the compressor described above. This set is enclosed in a tight housing, in the periphery of which there are nozzles for supplying the working fluid. It feeds tangentially to the set of disks and is forced to describe a spiral trajectory, in this case from the periphery to the center, slowing down on its way and releasing its energy to the set of disks, which is the rotor of the turbine. The fluid exits the turbine through its central orifice, where its motion moves tangentially to the axial axis. / 3 /.

A turbine is known, consisting of two sets of coaxial cylindrical rings rotating in the opposite direction about each other about a common axis. The process is the opposite of the process performed on the compressor of the same type described above. The working fluid passes through the coaxial rings of the two sets of high pressure and gradually gives off its energy to them. Variants of this turbine and compressor of the same type are possible. For example, one set of coaxial cylindrical rings is fixed and only the second rotates. In both the compressor and the turbine, fluid motion is possible, both from the periphery to the axis and also back - from the axis to the periphery. / 4 /

Known is a gas turbine engine, a single disc consisting of a rotating disk and a stationary cover disk. The rotating disk has a compressor section in its central portion, representing a radial / centrifugal / compressor and a turbine section in its peripheral portion. The rotating disc is fixedly connected to a shaft that transmits power to the users. The rotating disc, the compressor and turbine sections on the one hand, and the fixed disk on the other, enclose the combustion chamber, in which, in addition to the fuel, water can be injected by others through special pipes. The gas turbine engine was tested at the Sowuthwest Research Institute, USA. A 2004 Internet article /httD://www.swri.org/Default.htm/ describes a test of the above-mentioned gas turbine engine. / 5 /.

The disadvantages of the known designs are that the engine speed is limited by the exhaustion of the strength of the material of which the turbine is made, as it is the most heavily loaded element of the engine due to the centrifugal forces and the heavy temperature regime in which it operates . At the same time, due to the smaller outer diameter of the compressor, its peripheral speed is far lower than the optimum speed, i.e. compressor speeds close to those limited by the strength of its material cannot be reached. This limits the compression ratio, resulting in low overall engine efficiency. In addition, given that the combustion chamber is of the required dimensions, the diameter of the turbine increases too much compared to that of the compressor, further limiting the engine speed. The combustion chamber can be made to the required dimensions by expanding into a stationary disk, but this results in an additional rotation of the flow, twice at an angle of more than 90 °, which increases aerodynamic losses. Also, due to the impossibility of applying contact sliding seals, the loss of compressed air flow back into the compressor receiver is increased. In the construction of this gas turbine engine construction, a minimum distance between the rotor and the stator is required, resulting in a high precision of its construction, which makes it expensive to manufacture.

small gas turbine engines are connected by the impossibility of proportional reduction of the gaps, the peripheral seals of the compressors and turbines and hence the increased losses as well as the reduced efficiency compared to the large gas turbine engines.

Problems with

SUMMARY OF THE INVENTION

The problem to be solved is to create a gas turbine engine, in particular a small-sized gas turbine engine with minimal loss of compressed air leakage, thereby reducing engine size without changing the efficiency / efficiency.

The problem is solved by a gas turbine engine including a compressor and a turbine mounted on a connecting shaft, as well as a combustion chamber between them.

According to the invention, the compressor and the turbine are fixedly connected to each other by means of a connecting shaft made as a hollow shaft. The hollow shaft, in turn, is the outer wall of the combustion chamber. The compressor and the turbine are mounted on a fixed axis centrally located on the axis of symmetry of the gas turbine engine. The compressor guide and diffuser as well as the turbine guide are fixed to the fixed axis.

In a sub-variant embodiment, after the turbine, also to the fixed axis, there is a second, free turbine with a guiding apparatus in front of it, whereby a gear wheel is formed in the rear of the free turbine, engaged with a gear wheel, forming a gear to a transmission shaft for supplying energy to the consumer.

In another embodiment, the compressor is comprised of an internal and external rotor, as well as a turbine, respectively, of an internal and external rotor, wherein the internal rotor of the compressor is connected to the internal rotor of the turbine by an internal hollow shaft and the outer rotor of the compressor and the outer rotor the rotor of the turbine are connected to each other by an external hollow shaft, while between the outer and the inner rotor of the compressor a gear unit is mounted, which is mounted on the fixed axis, which performs the opposite rotation of the inner and outer ro op.

In another embodiment, the two compressor rotors and the two turbine rotors are driven in opposite directions by gears mounted between each pair of rotors, respectively of the compressor and the turbine and the external rotors of the turbine and compressor are connected to each other as a whole through a hollow shaft.

Alternatively, an additional compressor is mounted in front of the main compressor, with an external cylinder made as a whole with the cover disk of the main compressor and the main compressor attached to the turbine rim by a hollow shaft.

The compressor and the turbine, through their respective cover disc and crown, fixed to the hollow shaft, form the motor rotor, which is supported by the fixed axis.

In addition, the compressor may be centrifugal and / or axial, diagonal, radial-axial, axial-radial, Tesla type, Pavlik type, and the turbine may be centrifugal and / or axial, diagonal, axial-radial, radial -axis, Tesla type, Pavlichka type.

• ·

The advantages of the invention are that, thanks to the connection of the connecting shaft as a hollow shaft, the combustion chamber is located inside, together with the fuel injectors and spark plugs, as well as control sensors for monitoring the operation of the gas turbine engine. In addition, the hollow shaft is a thin-walled tube, which is why its first resonant frequency is far below the operating range of the engine itself, thus avoiding the harmful resonance phenomena characteristic of gas turbine engines. Depending on the type of compressor and the turbine, the inside of the hollow shaft can also accommodate the diffuser of the compressor, if needed, the turbine guide apparatus, the nozzle of the pipelines for supplying water, steam, alcohol, flammable fuels for starting gas turbine engine and others. In addition, these pipelines, ignition cables and control sensors, as well as mechanism levers, are arranged through specially designed grooves in the fixed axis of the gas turbine engine, which ensures the compactness of the structure. Also, due to the location of the combustion chamber in the space enclosed by the compressor, the hollow shaft, the turbine and the fixed axis, there is no need to seal their peripherals to the housing, thus reducing the loss of compressed air from their peripherals to zero. Since the diameter of the stationary axis is significantly smaller than the diameter of the periphery of the compressor and the turbine, the relative linear speeds of movement between them are also much smaller. These sections are not directly affected by the heated gases and the temperature deformations in them are minimal. Also, vibration deformations are much smaller compared to the compressor and turbine peripherals. This makes it possible to use labyrinth seals with very dense contact as well as contact sliding seals made of suitable contact materials such as graphite steel, graphite bronze and others. Particularly effective and promising for small-sized gas turbine engine designs is the option of air or magnetic bearings or a combination of them. In this case, the air required for the air bearings is withdrawn from the compressor, so no additional air is needed. This air also acts as a cooler for the suspension. This ensures minimal losses of compressed air and virtually maintenance-free and durable suspension. The construction of the gas turbine engine according to the invention is universal with respect to the type of compressor and turbine. Centrifugal, diagonal, axial, axial-radial, radial-axial, and Tesla type compressors may be used. The turbine may be centrifugal, axial, axial-radial, radial-axial, Tesla type, and combinations of these types. The variant of a gas turbine engine with a free turbine is suitable for use in land vehicles where a wide engine speed and high torque at low speeds are required.

DESCRIPTION OF THE FIGURES

The invention is explained in more detail by way of exemplary embodiments of the gas turbine engine shown in the accompanying drawings, where:

Figure 1 is a longitudinal sectional view of a basic first embodiment of a gas turbine engine according to the invention.

2 is a longitudinal sectional view of a sub-variant of the first embodiment of the gas turbine engine of FIG. 1 according to the invention.

Figure 3 is a longitudinal sectional view of a second embodiment of the gas turbine engine of Figure 1 according to the invention.

4 is a longitudinal section view of a first sub-variant of the second embodiment of the gas turbine engine of FIG. 3 according to the invention.

5 is a longitudinal section view of a second sub-variant of a second embodiment of the gas turbine engine of FIG. 3 according to the invention.

Figure 6 is a longitudinal sectional view of a third embodiment of the gas turbine engine of Figure 1 according to the invention.

7 is a longitudinal sectional view of a fourth embodiment of the gas turbine engine of FIG. 1 according to the invention.

8 is a longitudinal sectional view of a fifth embodiment of the gas turbine engine of FIG. 1 according to the invention.

EXAMPLES OF IMPLEMENTATION

The gas turbine engine of the invention shown in Figure 1 consists of a compressor 1 and a turbine 2 connected to each other by a hollow shaft 3. The compressor 1 includes in its variants an internal rotor 1.1, an external rotor 1.2, a guide apparatus 1.3, a diffuser 1.4, a roof drive 1.5, compressor stages 1.6, axle • ·

guidance apparatus 1.7 and bolts 1.8 connecting the cover disk 1.5 to the inner disk. The turbine 2 includes, in its variants, an internal 2.1 and an external rotor 2.2, a guide apparatus

2.3, additional free turbine 2.4, with a gear 2.5 to it, a cover disk 2.6 and a guide apparatus 2.7 of the additional free turbine 2.4. The hollow shaft, in turn, incorporates in the embodiments 3.1 internal and external hollow shaft 3.2. The compressor 1 and the turbine 2 are mounted on a fixed axis 4 centrally located on the axis of symmetry of the gas turbine engine. A tube sleeve 4.2 is inserted along the fixed axis 4 and a profile sleeve 4.1 is mounted between the compressor 1 and the turbine 2. In the space between compressor 1 and turbine 2, a combustion chamber 5 enclosed by the hollow shaft 3 is formed around the profile sleeve 4.1, which forms its outer wall. The combustion chamber 5 is fitted with a spark plug 5.1 and fuel injection nozzles 5.2, which are secured to the profile bushing 4.1. Each nozzle 5.2 is connected by a fuel line 6.1 with a channel 6 formed between the fixed axis 4 and the tube sleeve 4.2 or in the fixed axis itself 4. The diffuser 1.4 is fixedly connected to the profile sleeve 4.1. In the area of the diffuser 1.4 are the outlet nozzles of pipelines 6.3 and channels 6.2 for supplying water, water vapor, alcohol or a mixture thereof. All elements are covered by housing 7 including rear 7.1 and front mounting posts 7.2, as well as filter 7.3 of the compressor air intake 1. Compressor 1 and turbine 2 are supported by bearings 8 to the fixed axis 4. The combustion chamber 5 is insulated by seals 9 of the labyrinth or sliding type. When the seals 9 are sliding, respective rings 9.1 are packed in the compressor 1 and in the turbine 2, and graphite bushes 9.2, supported by flat springs 9.3, are mounted in the profile sleeve 4.1. In • 9 · «« 9 9 * · • · 9 · 99 99

9 9 · 9 99

9 9 t> 9 9 9 9 99

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9999 99 999 99 99 99999 The back of the housing 7 is formed by a nozzle 10. All the standard engine components, such as: gearboxes, starting motors, nozzle regulators, forcing system elements, are connected to the housing 7 or to the fixed axis 4. , power supply, electronic systems and more.

The difference from traditional schemes is that the radial / diagonal / compressor 1 is necessarily a coated type, with the cover disc 1.5 extending radially from its peripheral side to connect it to the hollow shaft 3 and through it to the turbine rim 2.

Figure 2 shows a sub-variant embodiment of the gas turbine engine of Figure 1. The engine elements of FIG. 1 described above are provided with a second, free turbine 2.4 with a guide apparatus 2.7 mounted behind the main turbine 2. A gear 2.5 is formed at the rear of the free turbine 2.4, engaged to the gear 11.1. of transmission shaft 11, which is used to transmit engine power to consumers. The compressor 1 is covered by a cover disk 1.5 fixed in its peripheral part to the front end of the hollow shaft 3. The gas turbine engine is closed by a housing 7 to which filters 7.3 are fitted at the inlet of the air intake in front of the guide unit 1.3 of the compressor 1. . The combustion chamber 5 is insulated by seals 9 of the labyrinth or sliding type, with sliding seals the corresponding rings 9.1 to the compressor 1 and the turbine 2 being stuffed, and graphite bushings 9.2 supported by flat springs 9.3 are mounted in the profile sleeve 4.1. The nozzle 10 is formed in the rear of the housing 7. Directly to the housing 7 or to the fixed axis 4 are all the associated standard engine elements, such as: gearboxes, starting motors, nozzle regulators, forcing system elements, power supply, electronic systems and more.

The difference from traditional gas turbine engine circuits is the same as for the gas turbine engine shown in Figure 1 described above.

In FIG. 3 is a second embodiment of the gas turbine engine of FIG. The compressor 1 is radial-axial, type Pavle, with a guide unit 1.3, as well as the turbine 2, with guide units 2.8 and 2.3, is also a type Pavlek. They are mounted by means of bearings 8 to the fixed axis 4, and between them is the combustion chamber 5 enclosed by the hollow shaft 3, which is integral with the compressor 1 and the turbine 2. It is firmly attached to the rear of the turbine 2 by the fixed axis 4 the guiding apparatus

2.3 of the turbine 2, as well as the first stage of the same 2.8, located in front of the first stage of the turbine 2. The spark plug 5.1 and the nozzles 5.2 are directly attached to the combustion chamber 5, whereby the nozzles 5.2, through pipes, are connected to a common central channel 6 made in the fixed axis 4. The compressor 1 and the turbine 2 are insulated by seals 9, and if they are sliding there is a packed ring 9.1 to the compressor 1 and to the turbine 2 as well as a graphite sleeve 9.2 supported by a flat spring 9.3.

The difference with traditional gas turbine engine schemes is that the hollow shaft compressor 1 and the turbine 2 are connected in a common engine structure.

4 shows a sub-variant of a second embodiment of the gas turbine engine of FIG. The compressor 1 and the turbine 2 are type Pavlec. The compressor 1 is two-rotor and includes an internal rotor 1.1 and an external rotor 1.2. The turbine 2 is also two-rotor and contains an internal rotor 2.1 and an external rotor 2.2. The internal rotor 1.1 of compressor 1 is connected to the inner rotor 2.1 of the turbine 2 via the inner hollow shaft 3.1, and the outer rotor 1.2 of the compressor 1 is

connected to the outer rotor 2.2 of the turbine 2 through the outer hollow shaft 3.2. In the space between the compressor 1 and the turbine 2 and inside the hollow shaft 3.1 are located the diffuser 1.4 and the combustion chamber 5, with its spark plug 5.1 and the nozzles 5.2 attached to the profile sleeve 4.1, to which the labyrinth pins 9 or slides are incorporated seals 9.1, 9.2 and 9.3. The labyrinth seals 9 formed therein are provided between the inner 2.1 and the outer rotor 2.2 of the turbine 2. The rotors 2.1 and 2.2 of the turbine 2 as well as the rotors 1.1 and 1.2 of the compressor 1 are mounted to the fixed axis 4 by means of bearings 8. A gear 12 is mounted between the bearings 8 of the compressor rotors 1.1 and 1.2.

The difference with traditional gas turbine engine circuits is that the opposite rotating pairs of compressor rotors 1.1 and

1.2 and a pair of turbine rotors 2.1 and 2.2 are connected by their respective inner 3.1 and outer hollow shaft 3.2.

Figure 5 is an exploded view of the gas turbine engine of Figure 4 described above. The following elements are disassembled: internal 1.1 and external rotor 1.2 of compressor 1, bearings 8, seals 9, gear 12, diffuser 1.4, all located in front of the combustion chamber 5 and its associated spark plug 5.1, nozzles 5.2 and the guiding apparatus 2.3. turbine 2. Behind the combustion chamber 5, also disassembled, are shown the inner hollow shaft 3.1, the outer hollow shaft 3.2, the sliding seals 9.1, 9.2 and 9.3, the bearings 8, the turbine itself 2, the labyrinth seal 9, formed in the outer 2.2 and the inner turbine rotor 2.1.

Figure 6 shows a third embodiment of the gas turbine engine of Figure 1. Compressor 1 is a two-axis axial, with internal 1.1 and external • is ♦ · · * »* ·

I 4 I · · · · · · · · · · · rotor 1.2, as well as turbine 2 is two-rotor, with internal 2.1 and external rotor 2.2, bearing 8 to the fixed axis 4. A diffuser 1.4 is mounted in front of the combustion chamber 5. connected to the profile sleeve 4.1, after which the spark plug 5.1 and the nozzles 5.2 are also attached to the profile sleeve 4.1. Nozzles 5.2 are connected via tubes to the central conduit 6 or a duct terminating with radial outlets. Toothed gears 12 are mounted to the fixed axis 4 between the two rotors 1.1 and 1.2 of the compressor 1 and between the two rotors 2.1 and 2.2 of the turbine 2, whereby the two rotors 1.1 and 1.2 of the ^w compressor 1 and the two rotors 2.1 and 2.2 of the turbine 2 rotate in opposite directions. They are all enclosed by the hollow shaft 3. Behind the turbine 2 is a support post 7.1 that connects the fixed axis 4 to the rear end of the housing 7, where the nozzle 10 is formed.

The difference with traditional gas turbine engine schemes is that the external rotors 1.2 and 2.2 of the compressor 1 and the turbine 2 are connected by means of a hollow shaft 3 which is extended at both ends to the compressor 1 and the turbine 2 respectively.

C Figure 7 shows a fourth embodiment of the gas turbine engine of Figure 1. The compressor is a composite type - axial-centrifugal / diagonal /, the first stage is an axial compressor 1.6, with a guide unit 1.7, and the second stage is a centrifugal / diagonal / compressor 1, with a guide unit 1.3. The compressor 1 is mounted 8 to the fixed axis 4, as is the turbine 2. The guide 2.3 of the turbine 2 is rigidly mounted to the fixed axis 4. Here, the turbine 2 is also two-stage. Between the compressor 1 and the turbine 2, behind the diffuser 1.4, there is a combustion chamber 5 with its spark plug 5.1 and nozzles 5.2, the latter being attached to the profile sleeve 4.1.

··· ························································· ············ with the labyrinth seals 9 or sliding seals 9.1, 9.2 and 9.3. Injectors 5.2, in turn, are connected by tubes to the grooves 6 formed between the surface of the fixed axis 4 and the inner surface of the stuffed sleeve 4.2. The combustion chamber 5 is enclosed by the hollow shaft 3 connected at the rear end with the turbine rim 2 and at the front end by the cover disk 1.5 of the compressor 1, elongated bilaterally and fixedly connected to the outer cylinder of the axial compressor 1.6. The axial compressor 1.7 guidance and radial / diagonal / compressor 1.3 guidance are fixed to the sleeve 4.2 crimped onto the shaft 4. The gas turbine engine is enclosed in housing 7 and secured by rear mounting posts 7.1 and front 7.2 connecting the housing 7 to the fixed housing 7 axis 4. Behind the turbine 2, a nozzle 10 is formed at the end of the housing 7.

The difference from the traditional schemes of the gas turbine engine is that the centrifugal / diagonal / stage cover 1.5 is bilaterally elongated and connected to the hollow shaft 3 in its peripheral part and through it to the turbine rim 2 and in its front forms the supporting shaft of the axial degree 1.6 of the compressor 1.

Figure 8 shows a fifth embodiment of the gas turbine engine of Figure 1. The compressor 1 and the turbine 2 are Tesla type and are mounted 8 to the fixed axis 4. Among them are the diffuser 1.4, the combustion chamber 5, with its spark plug 5.1 and the nozzles 5.2, all attached to the profile sleeve 4.1, as well as the labyrinth seals 9 or sliding seals 9.1,

9.2 and 9.3. The nozzles 5.2 are connected by tubes to the central channel 6 formed in the fixed axis 4. The front of the compressor 1 is elongated and represents a power shaft 11.2 to the user through a gear (not shown in the drawing) hooked to the gear tooth at the front end of ft · ft ft · * I ·· ft · ft ft ·· ft ft • ft ft ft ft ft ft ft • ft ft ft ft ft ft ft ··· »· ··········· gear shaft 11.2. Prior to the hints of compressor 1, a cover disk 1.5 is secured, bolted 1.8 to the rear disk of the compressor 1. The peripheral side of the cover disk 1.5 is fixedly connected to the hollow shaft 3, which extends into the outer wall of the combustion chamber 5, and is then also connected. stationary to turbine cover disk 2.6 2. Turbine 2 cover disk 2.6 is also secured to its inner disk by bolts 1.8. Taken together as a whole, the cover disk 1.5 of the compressor 1, the hollow shaft 3 and the cover disk 2.6 of the turbine 2 serve as the housing of the gas turbine engine in the case of a hull-free version thereof.

The difference with traditional gas turbine engine schemes is that the outer wall of the combustion chamber is a hollow shaft connecting the compressor and the turbine.

APPLICATION / APPLICATION / INVENTION

The operation of the gas turbine engine, shown as a basic, first embodiment of Figure 1 is as follows.

Air enters through filter 7.3 and guide 1.3 in compressor 1. There it accelerates and exits compressor 1 at a speed close to the peripheral speed of compressor 1. If compressor 1 has straight radial blades, the air compression does not increase, and if the blades are curved, the air is also compressed to some extent in the compressor itself 1. Then, the air exits radially or diagonally, depending on the type of compressor (radial or diagonal), after which the air direction changes in axial motion. in to Pouring diffuser 1.4. The diffuser 1.4 is a blade type. There, the air is slowing down and its pressure is increasing. The air pressure decreases and its pressure increases. to the extent that the engine is sized. Hence, the air enters the combustion chamber 5, where it is mixed with the fuel and the mixture ignited. The combustion mixture is heated and fed into the turbine guide 2.3. 2. The guide rail

2.3 rotate the heated gases at a suitable angle, and then they enter the turbine 2. There they hit their blades and rotate them, while expanding and accelerating. The heated gases are then introduced into the nozzle 10 of the engine, where they are further accelerated and expanded and vented into the atmosphere.

The elements of compressor 1 and turbine 2 connected at their periphery by the hollow shaft 3 form the rotor of the gas turbine engine. Its bearing can be made by means of roller bearings, and for small motors - ball bearings 8. Due to its high speeds, ceramic type bearings are suitable. For large engines, an axial bearing is also required to absorb the longitudinal force generated in the rotor by the reactive force generated by the leakage force. For small motors, these bearings can be replaced by air, magnetic or a combination of them, which is the most economical solution. When using air bearings, they also act as seals on the combustion chamber 5. The air is removed from the compressor 1. The seals can be labyrinth type 9 or sliding seals 9.1, 9.2 and 9.3. The labyrinth seals 9 are traditional for jet engines. The sliding seals 9 are formed by a clamped ring 9.1, a graphite sleeve 9.2 and a flat spring 9.3. Ring 9.1 is made of wear-resistant material with low friction and is crammed into the front of the axial bore of the turbine 2 or the back of the compressor 1. The graphite sleeve 9.2 is made of graphite, graphite bronze or t «« <· · f W • · · · · · · · · · · · · · · · · · · · · · · · · Other relevant materials. It is mounted tightly in a specially made hole in the profile sleeve 4.1, with the possibility of moving on the axis. The graphite sleeve 9.2 is pressed against the ring 9.1 of the flat spring 9.3 positioned behind the graphite sleeve 9.2, which is crammed into the bore of the compressor 1 and the turbine 2. Feed the fuel into the nozzles 5.2 through ducts 6 and pipelines 6.1. A spark plug is used for the initial ignition of the fuel 5.1. Water, alcohol, water vapor, or other suitable liquid is supplied to the combustion chamber 6.3 through the combustion chamber 5 to improve the operation of the gas turbine engine. This improves the economy of the engine and increases its power. It is also possible to inject water or steam into the blades of turbine 2 for cooling. When the cooling of the blades is air, the air is withdrawn from the compressor 1 and, through suitable channels, is introduced into the blades of the turbine 2. Water vapor injection is a particularly suitable and economically advantageous method for increasing the efficiency of the small gas turbine engines of the type according to the invention. The steam nozzle 10 of the engine is used as the steam generator and the steam is fed into the diffuser zone 1.4 of the compressor 1, in front of the combustion chamber 5 through the channels 6.2 executed in the fixed axis 4 and the conduits 6.1. The engine may have a housing 7 that serves as a support member. A filter 7.3 may be fitted at the air intake inlet. The guidance apparatus 1.3 and 2.3, respectively of the compressor 1 and the turbine 2, the diffuser 1.4, the combustion chamber 5 with the nozzles 5.2, the inlet tubes 6.3, as well as the sensors for monitoring the engine operating mode, are fixed to the fixed axis 4.

In the sub-embodiment of FIG. 2, the gas turbine engine of FIG. 1 has the same effect as in the basic, first embodiment of FIG. In this • "

V · • · case, turbine 2 is two-stage, the second stage is the free turbine 2.4. The first stage of the turbine 2 is fixedly connected to the compressor 1 through the hollow shaft 3 and is a compressor turbine. The free turbine 2.4 is connected by a gear 11.1 to a separate shaft 11, which transmits useful power to the user. This sub-variant of the gas turbine engine of Figure 1 is suitable for ground applications as well as for turbojet engines for airplanes and helicopters. Here, the free turbine 2.4 plays the role of and of a torque transformer with favorable ground transportation characteristics.

The operation of the second embodiment shown in Fig. 3 of the gas turbine engine of Fig. 1 is as follows.

Compressor 1 is radial-axial, type Paul, and turbine 2 is also type Paul.

The air enters radially from the periphery of the compressor 1 to the stationary axis 4, where it changes its direction to axial, and then, from the combustion chamber 5, the air enters the first stage 2.8 of the turbine 2's guide apparatus, passing successively through the stages of the turbine 2 and its guide apparatus 2.3, then discharged into the atmosphere. The combustion chamber 5, fuel supply, water, alcohol, steam, cooling, ignition, lubrication, controls, seals, suspension, and materials follow the same principles described in the basic, first embodiment of the gas turbine engine according to the invention.

The sub-variant of the gas turbine engine of FIG. 3 shown in FIGS. 4 and 5 is as follows.

The compressor 1 and the turbine 2 are two-rotor type Pavle. The two-rotor compressor 1 consists of an internal 1.1 and an external rotor 1.2, and a two-rotor turbine 2 consists of an internal 2.1 and an external rotor 2.2. The internal rotor 1.1 of the compressor 1 is connected to the inner rotor 2.1 of the turbine 2 via the inner hollow shaft 3.1, and the outer rotor 1.2 of the compressor 1 is connected to the outer rotor 2.2 of the turbine 2 via the outer hollow shaft 3.2.

The air enters axially into the compressor 1, where it compresses, and then, through the diffuser 1.4, is fed into the combustion chamber 5. Thereafter, the air passes through the guide apparatus 2.3 of the turbine 2, and then alternately between the blades of its inner rotor 2.1, the outer its rotor 2.2, again passes through the inner rotor 2.1, the outer rotor 2.2 and is ejected into the atmosphere through the nozzle 10. The internal 2.1 and the outer rotor 2.2 of the turbine 2, the inner 1.1 and the outer rotor 1.2 of the compressor 1, and the connecting internal 3.1 and outer hollow shaft 3.2 rotate counter circumferential directions made by a gear

12. In this way, the traditional Pawlichka scheme was modified, since the supply of air is done from the axis and the extraction of compressed air is realized from the periphery of the compressor 1. This increases the efficiency of the compressor 1 as its last stages are rotated. at a higher linear speed than the first stages. The air, in turn, has a higher density and, consequently, a higher temperature, which is why the speed of sound in it increases with each successive stage. This allows for higher compression ratios in subsonic compressors. In addition, the latter grades become more efficient than the former due to the higher linear speed, which is also a favorable condition.

Figure 5 shows, in an exploded view, the elements of the above-described sub-option of Figure 4.

In FIG. 6 shows a third embodiment of the gas turbine engine of FIG. The compressor 1 is a two-axis axial, the turbine 2 is also a two-axis.

The engine action is as follows. Air enters the axial compressor 1 axially and enters through the rotors 1.1 and 1.2 through the diffuser 1.4 into the combustion chamber 5. There it is mixed with the fuel, the resulting mixture ignited, heated and accelerated and fed through the guide 2.3 into the rotors 2.1 and 2.2 of the turbine 2. The heated gases are then discharged into the atmosphere through the nozzle 10. The two rotors 1.1 and 1.2 of the compressor 1 and the two rotors 2.1 and 2.2 of the turbine 2 are rotated in opposite directions by means of their respective gears 12, bearing to fixed axis 4. since and com the portfolio 1 and the turbine 2 are dvurotorni, their speed is coordinated well and are about two times lower than the same in the single-engine performance. Thus, the requirements for the materials of which they are made are lower, since the linear velocities of their peripherals are about twice as low. The combustion chamber 5, fuel supply, water, alcohol, water vapor, cooling, ignition, lubrication, controls, seals, suspension, and materials, follow the principles laid down in the basic, first embodiment of the gas turbine engine of FIG. 1 according to the invention .

Figure 7 shows a fourth embodiment of the gas turbine engine of Figure 1 according to the invention.

In front of the compressor 1, which is radial or diagonal, an axial compressor 1.6 with a guide device 1.7 is mounted.

The engine action is as follows.

The air enters axially into the axial compressor 1.6, where it compresses and is fed to the centrifugal / diagonal / compressor 1. Through the diffuser 1.3, then through the diffuser.

1.4, the air enters the combustion chamber 5, where it is mixed with the fuel, the mixture is ignited and heated, and is fed into the turbine 2 through the guide 2.3, and then expelled through the nozzle 10 into the atmosphere.

The combustion chamber 5, fuel supply, water, alcohol, water vapor, cooling, ignition, lubrication, controls, seals, suspension, and materials, follow the principles laid down in the basic, first embodiment of the gas turbine engine of FIG. 1 according to the invention .

8 is a fifth embodiment of the gas turbine engine of FIG. 1 according to the invention.

Compressor 1 and turbine 2 are Tesla type.

The air enters axially into the central opening of the compressor 1 and is withdrawn from its periphery, and then, through the diffuser 1.4, it enters the combustion chamber 5, where it is mixed with the fuel and heated. Then, through the guide 2.3, where it rotates tangentially to the blades of turbine 2, it enters the turbine 2 itself, describing a spiral trajectory from the periphery to its axis. The exhaust gases are discharged into the atmosphere through the central opening of the turbine 2, where it is formed. the nozzle 10. The rotor of the gas turbine engine is composed of compressor 1 and turbine 2, fixedly connected by the hollow shaft 3 and bearing to the stationary axis 4 through bearings 8. The seals are labyrinthine 9 or sliding 9.1,9.2 and 9.3, same as in basic Oia, the first engine variant. The combustion chamber 5, fuel supply, water, alcohol, water vapor, cooling, ignition, lubrication, controls, seals, suspension, as well as materials, follow the principles laid down in the basic, first embodiment of the gas turbine engine of Fig. 1. according to the invention.

The gas turbine engine combustion system can be any of the known types, for example axial or tubular (bottle type), fuel injection or evaporation, with additional supply of water or water, alcohol or a mixture of water and alcohol. To start the engine, a highly combustible fuel can be supplied during its start-up phase, by forming additional channels 6 in the fixed axis 4 and pipelines 6.1.

The materials used in the manufacture of the individual elements of the gas turbine engine according to the invention may be aluminum, magnesium, titanium alloys and stainless steel for compressor 1, its guide unit 1.3 and the diffuser 1.4. Nickel temperature-resistant superalloys are suitable for hollow shaft 3, turbine 2 and its guide apparatus 2.3, as well as for combustion chamber 5 and profile sleeve 4.1.

Other variants of combinations of the above types of compressors and turbines are also possible. In practice, almost all variants of known schemes of gas turbine engines are also feasible in the case of an engine with an external wall of the combustion chamber which permanently connects the compressor and the turbine according to the invention. In all cases, the advantages of sealing the combustion chamber along its inner perimeter are maintained, ie. near the fixed axis 4. This results in small linear velocities, small amplitudes of vibration from beating, small temperature variations of the dimensions. All this makes the proposed scheme suitable, especially for small gas turbine engines.

Typical of all variants of the gas turbine engine according to the invention is that the axis around which the rotor, consisting of a compressor, turbine and connecting shaft, rotates is the fixed axis 4, and the connecting shaft is a hollow shaft 3 forming the outer wall of the combustion camera 5.

The gas turbine engine according to the invention, in all its variants, has a simplified construction in which, by means of a suitably combined compressor and turbine, easy construction is achieved, as well as a high efficiency / efficiency / in operation.

Claims (9)

Patent Claims A gas turbine engine comprising a compressor and a turbine mounted on a connecting shaft, as well as a combustion chamber, characterized in that the compressor (1) and the turbine (2) are connected to each other by means of a connecting shaft made as a hollow shaft (3). /, comprising, as an external wall, the combustion chamber / 5 /, wherein the compressor / 1 / and the turbine / 2 / are mounted / 8 / to a fixed axis / 4 /, located centrally on the axis of symmetry of the engine itself. An engine according to claim 1, characterized in that after the turbine (2), also to the fixed axis (4), there is a bearing (8) a second, free turbine (2.4) with a guide apparatus (2.7) in front of it, wherein at the rear of the free turbine / 2.4 / there is a gear tooth / 2.5 /, engaged by a gear wheel / 11.1 /, forming a gear / 2.5,11.1 / to a gear shaft / 11 / for energy to the consumer. An engine according to claim 1, characterized in that the guide device (1.3) and the diffuser (1.4) of the compressor (1) as well as the guide device (2.3) of the turbine (2) are fixed to the fixed axis (4). Engine according to claims 1 and 3, characterized in that the compressor (1) is composed of an internal (1.1) and an external rotor (1.2), as well as a turbine (2), respectively, of an internal one (2.1) and an external one. a rotor / 2.2 /, wherein the internal rotor / 1.1 / of the compressor / 1 / is connected to the inner rotor / 2.1 / of the turbine / 2 / via an internal hollow shaft / 3.1 / and the outer rotor / 1.2 / of the compressor / 1 / and the outer rotor / 2.2 / of the turbine / 2 / are connected to each other by means of an external hollow shaft / 3.2 /, while between the outer / 1.2 / and the internal rotor / 1.1 / of the compressor / 1 / a gear train / 12 / is mounted to n the movable axis / 4 /. Engine according to claim 1 and 4, characterized in that the two rotors (1.1,1.2) of the compressor (1) and the two rotors (2.1,2.2) of the turbine (2) are driven in opposite directions by gears / 12 / mounted between each pair of rotors / 1.1,1.2 / and /2.1,2.2/ respectively on the compressor / 1 / and the turbine / 2 / and the external rotors / 1.2,2.2 / on the compressor / 1 / and the turbine / 2 / are attached to each other as a whole by means of an external hollow shaft / 3.2 /. Engine according to claim 1, characterized in that an additional compressor (1.6) is mounted in front of the compressor (1), with an external bearing cylinder made as a whole with the cover disk (1.5) of the compressor (1) and attached to the crown of the compressor. the turbine / 2 / through the hollow shaft / 3 /. An engine according to claim 1, characterized in that the compressor (1) and the turbine (2), through their respective cover disks (1.5,2.6), fixedly connected to the hollow shaft (3), form the rotor of the motor bearing (8). / to the fixed axis / 4 /. An engine according to any one of claims 1 to 7, characterized in that the compressor (1) is designed as centrifugal and / or axial, diagonal, radial-axial, axial-radial, Tesla type, Pavle type. An engine according to claims 1 to 7, characterized in that the turbine (2) is designed as centrifugal and / or axial, diagonal, axial-radial, radial-axial, Tesla type, Pavle type.