CN110273782A - A kind of Micro Turbine Jet Engine of two-sided NEW TYPE OF COMPOSITE impeller - Google Patents

Abstract

The invention discloses a kind of Micro Turbine Jet Engines of two-sided NEW TYPE OF COMPOSITE impeller, including activation member, rotatable parts, casing component, rectification part, activation member is set to before the casing component, rotatable parts are set to the activation member rear, rectification part is set to casing component rear, rotatable parts include two-sided NEW TYPE OF COMPOSITE impeller, main shaft, bearing, main shaft and two-sided NEW TYPE OF COMPOSITE impeller are seamless connected, two-sided NEW TYPE OF COMPOSITE impeller includes bilateral centrifugal compressor, bilateral centrifugal compressor wheel rim extension stretches place and is equipped with hollow axial flow turbine, bilateral centrifugal compressor is connected by two single centrifugal-flow compressors are back-to-back.Advantages of the present invention: the thermal efficiency improves, and oil consumption rate reduces；Micro Turbine Jet Engine axial dimension is reduced, and reduces extent of vibration, improves stability；Turbine inlet temperature can be improved using hollow turbine Cooling Design.

Description

A micro-turbojet engine with double-sided composite impeller

technical field

The invention relates to the technical field of turbojet engines, in particular to a miniature turbojet engine with double-sided novel composite impellers.

Background technique

At present, various types of micro-aircraft are developing rapidly, which also promotes the development of corresponding micro-turbojet engines. The traditional micro-turbojet engine technology is mature and widely used, but it has no regenerator and turbine cooling design, so it improves energy utilization and performance. limited, and thus cannot meet the needs of special-purpose micro-aircraft. Therefore, developing a high-quality micro-turbojet engine has become a research hotspot in this field. In order to increase its energy utilization rate and propulsion performance without a regenerator, a new double-sided composite impeller micro-turbojet engine proposed by the patent of the present invention is expected to greatly improve these problems. Its double-sided centrifugal compressor has two End air intake and heat transfer inside and outside the turbine wall, recovering the temperature of the turbine exhaust, which not only increases the heat recovery cycle but also increases the temperature before the turbine, which not only improves the thermal efficiency but also improves the thrust-to-weight ratio.

Contents of the invention

In order to solve the above-mentioned technical problems that the micro-turbojet engine has no regenerator to recover the turbine exhaust temperature and no turbine cooling design, and then cannot realize high energy utilization rate and high-performance micro-turbojet engine, the present invention provides a double-sided A micro-turbojet engine with a new compound impeller. It can better meet the use requirements of miniature turbojet engines such as miniature aircraft and missiles.

The present invention adopts the following technical scheme: a micro-turbojet engine with double-sided novel composite impellers, including a starting part, a rotating part, a casing part, and a rectifying part, the starting part is arranged before the casing part, and the rotating The component is arranged behind the starting part, the rectifying part is arranged behind the casing part, the rotating part includes a double-sided new composite impeller, a main shaft, and a bearing, and the main shaft is seamless with the double-sided new composite impeller Fixed connection, easy to process, beneficial to reduce weight, improve reliability, and reduce maintenance costs. The double-sided new composite impeller includes a double-sided centrifugal compressor, and the outer extension of the double-sided centrifugal compressor wheel rim is provided with a hollow Axial-flow turbine, the double-sided centrifugal compressor is fixed back-to-back by two single centrifugal compressors, the rectification component includes a tail nozzle, a hollow rectification strut, a rectification cone, and the tail nozzle, hollow rectification strut Plates and rectifying cones form a whole. The structural design of the micro-turbojet engine not only reduces the axial size, but also has a more compact structure and improved stability.

Preferably, the casing part includes a rectifying bracket, a casing, an annular combustion chamber, and a shaft sleeve, the main shaft is arranged in the shaft sleeve, and a bearing is sleeved on the main shaft, and the rectifying bracket and the casing They are arranged on the same axis, and the rectifier frame is fixedly connected with the end of the casing, and the annular combustion chamber is arranged inside the casing. The axial size of the annular combustion chamber is reduced to reduce the structural weight.

Preferably, the starting component includes a starter motor, a starter motor seat, and a clutch, the starter motor is fixedly connected to one end of the starter motor seat, and the other end of the starter motor seat is fixedly connected to the rectification bracket through bolts, and the starter motor is connected to the rectifier bracket through a clutch. connected to the spindle.

Preferably, a circular clamp is provided at the blade tip rim of the double-sided centrifugal compressor, and the root of the hollow axial flow turbine is seamlessly connected with the circular clamp and the double-sided centrifugal compressor. The double-sided new composite impeller has air intake at both ends, the flow rate is increased, the cooling effect of the turbine is improved, and the performance of the micro-turbojet engine is further improved.

Preferably, the single centrifugal compressor includes long blades, middle blades, and short blades, the radial maximum position of the long blades is seamlessly fixed with the circular clamp, and the radial maximum position of the middle blades is connected with the The circular clamp is seamlessly fixed, the radial maximum position of the short blade is seamlessly fixed with the circular clamp, and the radial maximum position of the long blade is seamlessly fixed with the hollow axial flow turbine. The radial maximum position of the blade mentioned above is seamlessly fixed to the hollow axial flow turbine, and the radial maximum position of the short blade is seamlessly fixed to the hollow axial flow turbine.

Preferably, the rectification component also includes a turbine guider, the turbine guider is arranged behind the annular combustion chamber, the basic element stage airfoil shape of the hollow rectifier strut is a symmetrical airfoil, and the tail nozzle and rectifier The cone is fixedly connected by a hollow rectifying support plate, and the tail nozzle is arranged behind the casing shell. It is easy to process, which is conducive to reducing weight, improving reliability and reducing maintenance costs.

Compared with the prior art, the present invention has the following advantages: 1. The micro-turbojet engine increases the heat recovery cycle on the basis of the Brayton cycle, that is, the heat transfer of the gas inside and outside the hollow turbine wall, recovers the heat from the turbine outlet, and improves the combustion chamber inlet. The total air temperature is lower, and the oil supply is reduced on the premise that the temperature in front of the turbine remains unchanged. Therefore, the thermal efficiency is improved and the fuel consumption rate is reduced; 2. The air intake at both ends of the double-sided centrifugal compressor increases the flow rate and the axial force is offset; 3. The axial size of the micro-turbojet engine is reduced, reducing the degree of vibration and improving stability; 4. The cooling design of the hollow turbine can increase the temperature before the turbine.

Description of drawings

Fig. 1 is the structure schematic diagram of micro-turbojet engine of the present invention.

Fig. 2 is a 3D perspective view of the micro-turbojet engine of the present invention.

Fig. 3 is a schematic diagram of the structural principle of the micro-turbojet engine of the present invention.

Fig. 4 is a structural schematic diagram of the double-sided novel composite impeller of the engine of the present invention.

Fig. 5 is a structural schematic diagram of the single centrifugal compressor of the engine of the present invention.

Explanation of reference numerals: 1, starting part; 2, casing part; 3, rotating part; 4, rectifying part; 1-1, starting motor; 1-2, clutch; 1-3, starting motor fixing seat; 2- 1. Shaft sleeve; 2-2. Rectifier bracket; 2-3. Case; 2-4. Annular combustion chamber; 3-1. Double-sided new composite impeller; 3-1-1. Double-sided centrifugal compressor; 3. -1-1-1, single centrifugal compressor; 3-1-1-1-1, long blade; 3-1-1-1-2, middle blade; 3-1-1-1-3, short Blade; 3-1-2, circular clamp; 3-1-3, hollow axial flow turbine; 3-2, main shaft; 3-3 bearing; 4-1, turbine guide; 4-2, tail nozzle; 4-3, hollow rectifying support plate; 4-4, rectifying cone; a, incoming air; b, high-pressure air; c, high-temperature gas; d, high-temperature and high-pressure air; e, low-temperature gas; f, rear intake air; g. External atmosphere; A. Hollow axial flow turbine cascade passage; B. Hollow axial flow turbine inner passage; D. Centrifugal compressor cascade passage.

Detailed ways

The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, so as to define the protection scope of the present invention more clearly.

In this embodiment, it should be understood that the terms "middle", "upper", "lower", "top", "right side", "left end", "above", "back", "middle", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation , and therefore cannot be construed as a limitation of the present invention.

Please refer to Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, a kind of miniature turbojet engine of double-sided novel composite impeller (3-1), including starting part (1), rotating part (3), casing component (2), rectifying component (4), the starting component (1) is set before the casing component (2), the rotating component (3) is set behind the starting component (1), and the The rectifying part (4) is arranged behind the casing part (2), and the rotating part (3) includes a double-sided new composite impeller (3-1), a main shaft (3-2), and a bearing (3-3), The main shaft (3-2) is seamlessly fixed with the double-sided novel composite impeller (3-1), which is convenient for processing, helps reduce weight, improves reliability, and reduces maintenance costs. The double-sided novel composite impeller ( 3-1) It includes a double-sided centrifugal compressor, and the outer extension of the rim of the double-sided centrifugal compressor is provided with a hollow axial flow turbine (3-1-3), and the double-sided centrifugal compressor is composed of two A single centrifugal compressor (3-1-1-1) is fixedly connected back to back, and the rectification component (4) includes a tail nozzle (4-2), a hollow rectification support plate (4-3), a rectification cone (4- 4), described exhaust pipe (4-2), hollow rectifying support plate (4-3), rectifying cone (4-4) form a whole, the structural design of this miniature turbojet engine not only reduces axial dimension, and Its structure is more compact, and its stability is also improved.

Preferably, the casing part (2) includes a rectifying bracket (2-2), a casing (2-3), an annular combustion chamber (2-4), a shaft sleeve (2-1), and the main shaft (3 -2) It is set in the shaft sleeve (2-1), and the bearing (3-3) is sleeved on the main shaft (3-2), and the shaft sleeve (2-1) is set in the rectification bracket (2- 2), the rectification bracket (2-2) and the casing (2-3) are arranged on the same axis, and the rectification frame is fixedly connected to the end of the casing (2-3), and the ring The combustion chamber (2-4) is arranged inside the casing (2-3). The axial dimension of the annular combustion chamber (2-4) is reduced to reduce the structural weight.

Preferably, the starting part (1) includes a starter motor (1-1), a starter motor (1-1) seat, a clutch (1-2), and the starter motor (1-1) is connected to the starter motor (1-1) 1) One end of the seat is fixedly connected, and the other end of the starter motor (1-1) seat is fixedly connected to the rectifier bracket (2-2) through bolts, and the starter motor (1-1) is connected to the The main shaft (3-2) is connected.

Preferably, a round clamp (3-1-2) is provided at the blade tip rim of the double-sided centrifugal compressor (3-1-1), and the root of the hollow axial flow turbine (3-1-3) is connected to The circular clamp (3-1-2) and the double-sided centrifugal compressor (3-1-1) are seamlessly connected. The double-sided novel composite impeller (3-1) has air intake at both ends, and the flow rate increases, which improves the cooling effect of the turbine and further improves the performance of the micro-turbojet engine.

Preferably, the single centrifugal compressor (3-1-1-1) includes long blades (3-1-1-1-1), middle blades (3-1-1-1-2), short blades (3-1-1-1-3), the radial maximum position of the long blade (3-1-1-1-1) is seamlessly fixed with the circular clamp (3-1-2), the The radial maximum position of the middle blade (3-1-1-1-2) is seamlessly fixed with the circular clamp (3-1-2), and the short blade (3-1-1-1- 3) The radial maximum position of the blade is seamlessly fixed with the circular clamp (3-1-2), and the radial maximum position of the long blade (3-1-1-1-1) is connected with the hollow axial flow The turbine (3-1-3) is seamlessly fixed, and the radial maximum position of the middle blade (3-1-1-1-2) is seamlessly fixed to the hollow axial flow turbine (3-1-3). The radial maximum position of the short blades (3-1-1-1-3) is seamlessly fixed with the hollow axial flow turbine (3-1-3).

Preferably, the rectification component (4) further includes a turbine guide (4-1), the turbine guide (4-1) is arranged behind the annular combustion chamber (2-4), and the hollow rectifier The plate (4-3) element-level airfoil is a symmetrical airfoil, the tail nozzle (4-2) and the rectifying cone (4-4) are fixedly connected through the hollow rectifying support plate (4-3), and the tail The spray pipe (4-2) is located at the rear of the casing (2-3). It is easy to process, which is conducive to reducing weight, improving reliability and reducing maintenance costs.

The present invention is achieved in that the incoming air (a) is pressurized into high-pressure air through a single centrifugal compressor (3-1-1-1), and (b) flows into the inner channel (B) of the hollow axial flow turbine wall and continues to expand. The high-pressure air (b) in the turbine wall and the high-temperature gas (c) outside the turbine wall generate heat transfer, that is, the high-temperature and high-pressure air (d) is discharged from the turbine wall, and then enters the annular combustion chamber (2-4) to mix with fuel Combustion discharges high-temperature gas (c), then drives the turbine through the cascade channel outside the turbine wall and discharges low-temperature gas (e), and finally ejects at high speed from the tail nozzle (4-2), and flows from the external atmosphere (g) through the hollow Rear intake air (f) is formed behind the inner cavity of the rectifying support plate (4-3), and the working condition of the rear intake air is the same as above (f) in the same way.

It is not limited thereto, and any changes or replacements that do not go through creative efforts shall fall within the scope of protection of the present invention. Therefore, the protection scope of the present invention should be determined by the protection scope defined in the claims.

Claims (6)

1. a kind of miniature turbojet engine of double-sided novel compound impeller (3-1), it is characterized in that, comprises starting part (1), rotating part (3), casing part (2), rectifying part (4), The starting part (1) is arranged in front of the casing part (2), the rotating part (3) is arranged behind the starting part (1), and the rectifying part (4) is arranged in the casing Behind the component (2), the rotating component (3) includes a double-sided novel composite impeller (3-1), a main shaft (3-2), and a bearing (3-3), and the main shaft (3-2) and the The double-sided novel composite impeller (3-1) is seamlessly connected, and the double-sided novel composite impeller (3-1) includes a double-sided centrifugal compressor, and the outer extension of the double-sided centrifugal compressor wheel rim is provided with Hollow axial flow turbine (3-1-3), the double-sided centrifugal compressor is connected back to back by two single centrifugal compressors (3-1-1-1), and the rectification component (4) includes a tail Nozzle (4-2), hollow rectifying strut (4-3), rectifying cone (4-4), described tail nozzle (4-2), hollow rectifying strut (4-3), rectifying cone ( 4-4) Form a whole. 2. the miniature turbojet engine of double-sided novel composite impeller (3-1) according to claim 1, is characterized in that, described casing part (2) comprises rectifying bracket (2-2), casing (2) -3), annular combustion chamber (2-4), shaft sleeve (2-1), the described main shaft (3-2) is arranged in the shaft sleeve (2-1), and on the described main shaft (3-2) A bearing (3-3) is sleeved, the shaft sleeve (2-1) is set in the rectifying bracket (2-2), and the rectifying bracket (2-2) and the casing (2-3) are arranged On the same axis, and the rectifying frame is fixedly connected with the end of the casing (2-3), and the annular combustion chamber (2-4) is arranged inside the casing (2-3). 3. the miniature turbojet engine of double-sided novel composite impeller (3-1) according to claim 1, is characterized in that, described start-up part (1) comprises starter motor (1-1), starter motor (1-1) 1) Seat, clutch (1-2), the starter motor (1-1) is fixedly connected to one end of the starter motor (1-1) seat, and the other end of the starter motor (1-1) seat is connected to the rectification bracket through bolts (2-2) is fixedly connected, and the starter motor (1-1) is connected to the main shaft (3-2) through a clutch (1-2). 4. the miniature turbojet engine of double-sided novel composite impeller (3-1) according to claim 1, is characterized in that, described double-sided centrifugal compressor (3-1-1) blade tip wheel rim place is provided with A circular clamp (3-1-2), the root of the hollow axial flow turbine (3-1-3) and the circular clamp (3-1-2), double-sided centrifugal compressor (3-1-1 ) are seamlessly fixed. 5. the miniature turbojet engine of double-sided novel composite impeller (3-1) according to claim 1, is characterized in that, described single centrifugal air compressor (3-1-1-1) comprises long blade (3 -1-1-1-1), middle blade (3-1-1-1-2), short blade (3-1-1-1-3), the long blade (3-1-1-1 -1) The radial maximum position is seamlessly fixed with the circular clamp (3-1-2), and the radial maximum position of the middle blade (3-1-1-1-2) is seamlessly connected with the circular clamp The hoop (3-1-2) is seamlessly fixed, and the radial maximum position of the short blade (3-1-1-1-3) is seamlessly fixed with the round hoop (3-1-2) , the radial maximum position of the long blade (3-1-1-1-1) is seamlessly fixed with the hollow axial flow turbine (3-1-3), and the middle blade (3-1-1- The radial maximum position of 1-2) is seamlessly fixed with the hollow axial flow turbine (3-1-3), and the radial maximum position of the short blade (3-1-1-1-3) is connected with the The hollow axial flow turbine (3-1-3) is seamlessly fixed. 6. the miniature turbojet engine of double-sided novel compound impeller (3-1) according to claim 1, is characterized in that, described rectifying part (4) also comprises turbine guider (4-1), and described turbine The guide (4-1) is arranged behind the annular combustion chamber (2-4), the basic element stage airfoil of the hollow rectifying strut (4-3) is a symmetrical airfoil, and the tail nozzle (4- 2) It is fixedly connected with the rectifying cone (4-4) through a hollow rectifying support plate (4-3), and the tail nozzle (4-2) is arranged behind the housing of the casing (2-3).