CN214741683U - Double-sided composite impeller turbine engine based on gas drive blades - Google Patents

Abstract

The utility model discloses a two-sided compound impeller turbine engine based on gas drive paddle, including starting part, rotating part, machine casket part and exhaust nozzle, the utility model discloses light in weight, the gas drive paddle of gas drive paddle formula two-sided compound impeller turbine engine links firmly with the low pressure turbine for the engine axial dimension shortens substantially, has removed the required transmission part of traditional miniature turbine turboprop engine, very big lightening miniature turbine turboprop engine weight, improves the engine thrust-weight ratio; the utility model discloses compact structure moves the gas drive paddle to the middle part from the engine afterbody and makes with low pressure turbine an organic whole, compares in traditional miniature turbine turboprop engine and has reduced part figure, has simplified manufacturing process, effectual reduce cost, the later maintenance of being convenient for simultaneously.

Description

Double-sided composite impeller turbine engine based on gas drive blades

Technical Field

The utility model relates to a turbine engine technical field especially relates to a two-sided compound impeller turbine engine based on gas drive paddle.

Background

The micro turbine engine is widely applied to the fields of cruise missiles, light airplanes, remote control aircrafts, target planes and the like, and in order to meet the requirement of the aircrafts on continuously improved power performance, the micro turbine engine also needs to be continuously upgraded and improved. The traditional micro free-type turbine turboprop engine is advanced in technology and accepted by the market, but the design of a heat regenerator or the reason that the weight of the heat regenerator is higher are avoided, so that the improvement of the thermal efficiency and the thrust-weight ratio is greatly hindered, and the requirement of the market on the advanced micro free-type turbine turboprop engine technology cannot be met. The research focus in the field is that the weight of the miniature turboprop engine is reduced, and the thrust-weight ratio and the quick starting capability of the engine are improved. Therefore the utility model provides a two-sided compound impeller turbine engine based on gas drive paddle.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to solve the technical problem who exists among the prior art, provide a two-sided compound impeller turbine engine based on gas drive paddle.

In order to achieve the above purpose, the utility model provides a technical scheme is: a double-sided composite impeller turbine engine based on a gas drive blade comprises a starting part, a rotating part, a casing part and a tail nozzle, wherein one end of the casing part is connected with the starting part, the other end of the casing part is connected with the rotating part, the rotating part is connected with the tail nozzle, the tail nozzle comprises a rear air pipe I and a rear air pipe II, the rotating part comprises a double-sided composite impeller, a main shaft, a low-pressure turbine, an outer bearing and a gas drive blade, the double-sided composite impeller is arranged in the casing part, the gas drive blade is fixedly connected with the low-pressure turbine, the root of the gas drive blade is connected with the tail nozzle through the outer bearing, the low-pressure turbine, the outer bearing and the gas drive blade are positioned between the rear air pipe I and the rear air pipe II, the rear air pipe I is arranged between the double-sided composite impeller and the gas drive blade, and the rear air inlet pipe II is arranged at the tail part of the tail spray pipe.

Preferably, the jet nozzle further comprises a jet nozzle wall and a rear support, the rear support comprises a rear support shaft sleeve and a rear support plate, the rear support shaft sleeve is located on the main shaft, the rear support shaft sleeve is coaxial with the main shaft, and the rear support plate is connected with the inner wall of the jet nozzle.

Preferably, the casing part further comprises a casing and a rectifying support plate, the rectifying support plate is connected with the casing, a shaft sleeve is arranged in the rectifying support plate, an annular combustion chamber is arranged in the casing, and a hollow outer wheel guide blade is arranged at an outlet of the annular combustion chamber.

Preferably, the starting component comprises a starting motor fixed support and a clutch; the starting motor fixing support is provided with a starting motor, the starting motor and the main shaft are in transmission through the clutch, and the starting motor fixing support is arranged on the rectifying support plate.

Preferably, the double-sided composite impeller comprises a double-sided centrifugal compressor, a hollow axial high-pressure turbine, a circular hoop and a sealing ring; the hollow axial high-pressure turbine is arranged at the radial maximum position of the double-sided centrifugal compressor, the root of the hollow axial high-pressure turbine is in seamless connection with the circular hoop, and the sealing ring is arranged at the blade tip of the hollow axial high-pressure turbine.

Preferably, the double-sided centrifugal compressor comprises two single centrifugal compressors, and each single centrifugal compressor comprises a main blade and a splitter blade; the radial maximum positions of the main blade and the splitter blade are fixedly connected with the circular hoop in a seamless mode; the radial maximum positions of the main blade and the splitter blade are in seamless fixed connection with the hollow axial high-pressure turbine.

The utility model discloses beneficial effect:

1. the utility model discloses weight is little, and the two-sided compound impeller turbine engine's of air-driving paddle formula air-driving paddle links firmly with the low pressure turbine for engine axial dimension shortens substantially, has got rid of the required transmission part of traditional miniature turbine turboprop engine, very big has alleviateed miniature turbine turboprop engine weight, improves the engine thrust-weight ratio.

2. The utility model discloses compact structure moves the gas drive paddle to the middle part from the engine afterbody and makes with low pressure turbine an organic whole, compares in traditional miniature turbine turboprop engine and has reduced part figure, has simplified manufacturing process, effectual reduce cost, the later maintenance of being convenient for simultaneously.

3. The utility model discloses the reliability is high, and the two-sided compound impeller turbine engine of air drive paddle formula passes through the high-speed rotation of spun gas direct drive low pressure turbine and paddle in the quick-witted casket part, for the miniature turboprop engine of tradition, has avoided the instability and the complexity of gear box, has improved miniature engine's operational reliability.

4. The utility model discloses starting characteristic is good, and this micro engine can accelerate the gas combustion in the quick-witted casket part through going back to heat the increase on the one hand, improves fuel energy conversion efficiency, and the two-sided composite impeller of on the other hand can keep not under same rotational speed with the gas drive paddle, and the maintainability is simple and convenient, and starting characteristic is good, and it is big to start the envelope curve scope aloft, small in noise.

Drawings

The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it.

Fig. 1 is a schematic 3D perspective view of an air-driven blade type double-sided compound impeller turbine engine according to a preferred embodiment of the present invention;

FIG. 2 is a schematic view of the structural principle of the air-driven blade type double-sided composite impeller turbine engine of the present invention;

FIG. 3 is a schematic structural view of a double-sided composite impeller according to a preferred embodiment of the present invention;

FIG. 4 is a schematic structural view of a preferred embodiment of the present invention;

fig. 5 is a schematic structural view of a low-pressure turbine and blades according to a preferred embodiment of the present invention.

The attached drawings are marked as follows:

1. the device comprises a starting component 2, a rotating component 3, a casing component 4, a tail nozzle 1-1, a starting motor 1-2, a clutch 1-3, a fixed support 2-1, a double-sided composite impeller 2-2, a main shaft 2-3, a low-pressure turbine 2-4, an outer bearing 2-5, a gas drive blade 2-1-1, a double-sided centrifugal compressor hoop 2-1-2, a circular hoop 2-1-3, a hollow axial high-pressure turbine 2-1-4, a sealing ring 3-1, a shaft sleeve 3-2, a rectifying support plate 3-3, a casing 3-4, an annular combustion chamber 3-5, a hollow turbine guide vane 4-1, a rear gas inlet pipe I4-2, a rear gas inlet pipe II 4-3, a tail nozzle pipe wall 4-4, a rear support seat 4-4-1, 4-4-2 of a rear supporting seat shaft sleeve and a rear supporting seat supporting plate.

Detailed Description

This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

Referring to fig. 1-3, in a preferred embodiment of the present invention, a double-sided composite impeller turbine engine based on a gas-driven impeller comprises a starting part 1, a rotating part 2, a casing part 3 and a tail nozzle 4, wherein one end of the casing part 3 is connected to the starting part 1, the other end of the casing part 3 is connected to the rotating part 2, the rotating part 2 is connected to the tail nozzle 4, the tail nozzle 4 comprises a rear air inlet pipe i 4-1 and a rear air inlet pipe ii 4-2, the rotating part 2 comprises a double-sided composite impeller 2-1, a main shaft 2-2, a low-pressure turbine 2-3, an outer bearing 2-4 and a gas-driven impeller 2-5, the main shaft (2-2) and the double-sided composite impeller (2-1) are integrally manufactured to form a whole, the double-sided composite impeller 2-1 is arranged inside the casing part 3, the gas-driven blades 2-5 are fixedly connected with the low-pressure turbine 2-3 in an integrated manner, the number of transmission parts of a traditional micro turboprop engine is reduced, the weight of the engine is greatly reduced, the thrust-weight ratio is improved, the roots of the gas-driven blades 2-5 are connected with the tail nozzle 4 through the outer bearings 2-4, the outer bearings 2-4 are embedded into the tail nozzle 4, the low-pressure turbine 2-3, the outer bearings 2-4 and the gas-driven blades 2-5 are located between the rear air inlet pipe I4-1 and the rear air inlet pipe II 4-2, the rear air inlet pipe I4-1 is arranged between the double-faced composite impeller 2-1 and the gas-driven blades 2-5, and the rear air inlet pipe II 4-2 is arranged at the tail part of the tail nozzle 4.

The utility model has small weight, the gas-driven blade 2-5 of the gas-driven blade type double-sided composite impeller turbine engine is fixedly connected with the low-pressure turbine 2-3, so that the axial size of the engine is greatly shortened, the transmission parts required by the traditional miniature turbine turboprop engine are removed, the weight of the miniature turbine turboprop engine is greatly reduced, and the thrust-weight ratio of the engine is improved; the structure is compact, the gas drive blades 2-5 are moved from the tail part to the middle part of the engine and are integrally manufactured with the low-pressure turbine 2-3, compared with the traditional micro turbine turboprop engine, the number of parts is reduced, the processing and manufacturing process is simplified, the cost is effectively reduced, and meanwhile, the later maintenance is facilitated; the utility model has high reliability, the engine of the utility model directly drives the low-pressure turbine 2-3 and the gas-driven blade 2-5 to rotate at high speed through the gas sprayed out of the casing part 3, and compared with the traditional miniature turboprop engine, the instability and complexity of the traditional gear box are avoided, and the working reliability of the miniature engine is improved; the utility model discloses start-up characteristic is good, often require the start-up time control of engine within 10 seconds to microminiature turbine engine especially for bullet microminiature turbine engine, this micro engine on the one hand can accelerate the combustion of gas in the quick-witted casket part 3-3 through the increase of heat, has improved fuel energy conversion efficiency, and on the other hand two-sided composite impeller 2-1 can keep not under same rotational speed with gas drive paddle 2-5, and the maintainability is simple and convenient, and start-up characteristic is good, and aerial start envelope curve scope is big, small in noise.

As a preferred embodiment of the present invention, it may also have the following additional technical features:

in this embodiment, the tail pipe 4 further includes a tail pipe wall 4-3 and a rear support base 4-4, the rear support base 4-4 includes a rear support base shaft sleeve 4-4-1 and a rear support base support plate 4-4-2, the rear support base shaft sleeve 4-4-1 is located on the main shaft 2-2, the rear support base shaft sleeve 4-4-1 is coaxial with the main shaft 2-2, and the rear support base support plate 4-4-2 is fixedly connected with the inner wall of the tail pipe 4.

In this embodiment, the casing part 3 further includes a casing 3-3 and a rectifying support plate 3-2, the rectifying support plate 3-2 is fixedly connected with the casing 3-3, the rectifying support plate 3-2 and the casing 3-3 are on the same axis, a shaft sleeve 3-1 is arranged in the rectifying support plate 3-2, an annular combustion chamber 3-4 is arranged in the casing 3-3, a hollow outer wheel guide blade 3-5 is arranged at an outlet of the annular combustion chamber 3-4, and the annular combustion chamber 3-4, the hollow turbine guide blade 3-5 and the casing 3-3 are integrally manufactured, so that the manufacturing difficulty can be reduced, and redundant assembly stress can be avoided.

In the embodiment, the starting component 1 comprises a starting motor fixed support 1-3 and a clutch 1-2; the starting motor fixing support 1-3 is provided with a starting motor 1-1, the starting motor 1-1 and the main shaft 2-2 are in transmission through the clutch 1-2, and the starting motor fixing support 1-3 is arranged on the rectifying support plate 3-2.

In the embodiment, the double-sided composite impeller 2-1 comprises a double-sided centrifugal compressor 2-1-1, a hollow axial high-pressure turbine 2-1-3, a circular hoop 2-1-2 and a sealing ring 2-1-4; the hollow axial high-pressure turbine 2-1-3 is arranged at the radial maximum position of the double-sided centrifugal compressor 2-1-1, the root of the hollow axial high-pressure turbine 2-1-3 is in seamless connection with the circular hoop 2-1-2, the sealing ring 2-1-4 is arranged at the blade tip of the hollow axial high-pressure turbine 2-1-3, the heat exchange phenomenon of the air flow inside and outside the wall of the hollow axial high-pressure turbine 2-1-3 is generated, the outlet heat value of the turbine is recovered, the total air temperature of the inlet of the combustion chamber is improved, and the oil supply amount can be reduced. Effectively improving the heat efficiency and reducing the oil consumption rate.

In the embodiment, the double-sided centrifugal compressor 2-1-1 comprises two single centrifugal compressors which are fixedly connected back to back, and each single centrifugal compressor comprises a main blade and a splitter blade; the radial maximum positions of the main blade and the splitter blade are in seamless fixed connection with the circular hoop 2-1-2; the radial maximum positions of the main blades and the splitter blades are in seamless fixed connection with the hollow axial high-pressure turbine 2-1-3, so that the working state is more stable.

The utility model discloses a concrete theory of operation: incoming air is divided into front inlet air and rear inlet air, the rear inlet air comes from a rear inlet air pipe I4-1 and a rear inlet air pipe II 4-2, the incoming air is acted by a single centrifugal compressor to be boosted into high-pressure air which flows into a channel in the wall of a hollow axial high-pressure flow turbine 2-1-3 to be continuously diffused, the high-pressure air in the wall of the hollow axial high-pressure flow turbine 2-1-3 and high-temperature gas outside the wall of the hollow axial high-pressure flow turbine 2-1-3 generate heat transfer, namely the high-temperature high-pressure air is discharged, then the high-temperature high-pressure air enters a casing 3-3 to be divided into two air flows, one air flow enters an annular combustion chamber 3-4 from the upper part of the annular combustion chamber 3-4 to be mixed with fuel oil for combustion to discharge the high-temperature gas, the other air flow passes through the inner wall of a guide vane 3-5 of the hollow turbine to be subjected to heat exchange with the high-temperature gas discharged from the outside the wall, then enters an annular combustion chamber 3-4 for combustion; the high-temperature gas discharged from the annular combustion chamber 3-4 is firstly guided by the double-sided composite impeller 2-1 and then passes through the outer wall of the rear air inlet pipe I4-1, and then directly drives the low-pressure turbine 2-3 and the gas drive blades 2-5 to rotate, so that the double-sided composite impeller (2-1) turbine engine works normally, and finally the gas is subjected to heat exchange by the outer wall of the rear air inlet pipe II 4-2 and then is discharged as tail gas.

The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.

The above is only the preferred embodiment of the present invention, as long as the technical solution of the purpose of the present invention is realized by the substantially same means, all belong to the protection scope of the present invention.

Claims (6)

1. The utility model provides a two-sided compound impeller turbine engine based on gas drive paddle which characterized in that: the device comprises a starting part (1), a rotating part (2), a casing part (3) and a tail nozzle (4), wherein one end of the casing part (3) is connected with the starting part (1), the other end of the casing part (3) is connected with the rotating part (2), the rotating part (2) is connected with the tail nozzle (4), the tail nozzle (4) comprises a rear air inlet pipe I (4-1) and a rear air inlet pipe II (4-2), the rotating part (2) comprises a double-faced composite impeller (2-1), a main shaft (2-2), a low-pressure turbine (2-3), an outer bearing (2-4) and an air driving blade (2-5), the double-faced composite impeller (2-1) is arranged inside the casing part (3), and the air driving blade (2-5) is fixedly connected with the low-pressure turbine (2-3), the root of the gas drive blade (2-5) is connected with the tail nozzle (4) through an outer bearing (2-4), the low-pressure turbine (2-3), the outer bearing (2-4) and the gas drive blade (2-5) are located between the rear intake pipe I (4-1) and the rear intake pipe II (4-2), the rear intake pipe I (4-1) is arranged between the double-faced composite impeller (2-1) and the gas drive blade (2-5), and the rear intake pipe II (4-2) is arranged at the tail part of the tail nozzle (4).

2. The double-sided compound impeller turbine engine based on the gas drive blade as claimed in claim 1, wherein: the tail nozzle (4) further comprises a tail nozzle wall (4-3) and a rear supporting seat (4-4), the rear supporting seat (4-4) comprises a rear supporting seat shaft sleeve (4-4-1) and a rear supporting seat support plate (4-4-2), the rear supporting seat shaft sleeve (4-4-1) is located on the main shaft (2-2), the rear supporting seat shaft sleeve (4-4-1) is coaxial with the main shaft (2-2), and the rear supporting seat support plate (4-4-2) is connected with the inner wall of the tail nozzle (4).

3. The double-sided compound impeller turbine engine based on the gas drive blade as claimed in claim 1, wherein: the casing part (3) further comprises a casing (3-3) and a rectifying support plate (3-2), the rectifying support plate (3-2) is connected with the casing (3-3), a shaft sleeve (3-1) is arranged in the rectifying support plate (3-2), an annular combustion chamber (3-4) is arranged in the casing (3-3), and a hollow outer wheel guide blade (3-5) is arranged at the outlet of the annular combustion chamber (3-4).

4. The double-sided compound impeller turbine engine based on the gas drive blade as claimed in claim 3, wherein: the starting component (1) comprises a starting motor fixed support (1-3) and a clutch (1-2); the starting motor fixing support (1-3) is provided with a starting motor (1-1), the starting motor (1-1) and the main shaft (2-2) are transmitted through the clutch (1-2), and the starting motor fixing support (1-3) is arranged on the rectifying support plate (3-2).

5. The double-sided compound impeller turbine engine based on the gas drive blade as claimed in claim 1, wherein: the double-sided composite impeller (2-1) comprises a double-sided centrifugal compressor (2-1-1), a hollow axial high-pressure turbine (2-1-3), a circular hoop (2-1-2) and a sealing ring (2-1-4); the hollow axial high-pressure turbine (2-1-3) is arranged at the radial maximum position of the double-sided centrifugal compressor (2-1-1), the root of the hollow axial high-pressure turbine (2-1-3) is in seamless connection with the circular hoop (2-1-2), and the sealing ring (2-1-4) is arranged at the blade tip of the hollow axial high-pressure turbine (2-1-3).

6. The double-sided compound impeller turbine engine based on the gas drive blade as claimed in claim 5, wherein: the double-sided centrifugal compressor (2-1-1) comprises two single centrifugal compressors, and each single centrifugal compressor comprises a main blade and a splitter blade; the radial maximum positions of the main blade and the splitter blade are fixedly connected with the circular hoop (2-1-2) in a seamless mode; the radial maximum positions of the main blades and the splitter blades are seamlessly and fixedly connected with the hollow axial high-pressure turbine (2-1-3).

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