Ultrahigh-pressure-ratio compact efficient energy-saving turbojet engine

Abstract

The invention relates to an ultrahigh-pressure-ratio compact efficient energy-saving turbojet engine which comprises a main body part, a two-stage supercharging unit, a three-stage supercharging combustion unit and a reel structure connecting pipeline system. The reel structure connecting pipeline system comprises a first reel structure connecting pipeline, a second reel structure connecting pipeline, a third reel structure connecting pipeline and a fourth reel structure connecting pipeline. Along with the increase of the supercharge ratio, combusted gas expands and does work more sufficiently in the turbine, heat energy generated after fuel is combusted is converted into mechanical energy more effectively, the fuel oil heat efficiency is greatly improved, the fuel oil economical efficiency is improved, and fuel oil consumption is greatly reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace turbojet engine centrifuge design, and in particular relates to an ultra-high pressure ratio compact, high-efficiency and energy-saving turbojet engine. Background Art

[0002] Small turbojet engines have the characteristics of small size and light weight. Due to their small component size and overall size, they are widely used in military and civilian aircraft. In the military field, small engines can be used for training target aircraft, small military unmanned reconnaissance aircraft, cruise missiles, etc. They play an important role in improving operational flexibility, conducting reconnaissance to obtain intelligence efficiently, and achieving precision, and are of great significance to maintaining national security. In the civilian field, small turbojet engines are used in high-end model aircraft sports, small manned aircraft, flying backpacks, etc., and their application prospects are very broad.

[0003] The compressor is located between the air intake and the combustion chamber structure of the aviation turbojet engine. Its function is to compress the air entering the engine, thereby increasing the pressure and density of the air and providing high-pressure gas for the subsequent combustion process. Existing compressors are divided into axial flow compressors and centrifugal compressors based on their working principles. Axial flow compressors contain multiple stages. The more stages there are, the greater the compression ratio. However, the single-stage axial flow compressor has weaker supercharging capacity than the single-stage centrifugal compressor.

[0004] The biggest feature of the existing small turbojet engine is that the overall volume is small, so the size of each component is reduced. Due to the limitation of volume, the use of axial flow multi-stage compressor greatly increases the overall length and weight of the engine. Therefore, in order to ensure a certain overall volume, centrifugal compressors are mostly used, and the common single-stage structure causes the air to not be highly pressurized in the compressor, resulting in a low total pressure ratio. Therefore, due to the limited compression ratio, the gas entering the combustion chamber cannot be fully compressed, resulting in an unsatisfactory mixing of fuel and air, bringing about the problem of low engine thermal efficiency, which in turn leads to poor fuel economy. In addition, it will also lead to problems such as insufficient engine thrust and insufficient high-altitude flight performance. In response to these problems, in order to improve the compression ratio of small turbojet engines, improve thermal efficiency, reduce fuel consumption, and achieve the advantages of high efficiency and energy saving; at the same time, the engine thrust level is improved, thereby improving the performance level of small turbojet engines, based on the innovative design of the engine structure, the above problems are optimized. Summary of the invention

[0005] The purpose of the present invention is to solve the main problems that the existing small turbojet engine single-stage centrifugal compressor relies on only one-stage centrifugal impeller to compress the air, and the pressure ratio is limited, and it is difficult to compress the air to a higher pressure multiple, resulting in low engine thermal efficiency, increased fuel consumption, and poor fuel economy. A small three-stage centrifugal turbojet engine configuration is proposed. By making a new and innovative design of the traditional turbojet engine structure and layout, the air is compressed with a high amplitude after entering the engine, and has the characteristics of high pressure ratio, high gas utilization rate, and high thrust, which is of great significance for improving the performance of small turbojet engines.

[0006] The idea of ​​the present invention is to design a double-surround multi-stage centrifuge structure, change the direction of the centrifugal compressor, and connect the secondary boost unit and the main part, the secondary boost unit and the third-stage boost combustion unit through a scroll pipe. The main part and the secondary boost unit are designed with a volute-shaped structure to ensure that all the gas flowing out of the main centrifugal impeller enters the secondary boost unit, and to ensure that all the gas pressurized by the secondary centrifugal compressor enters the third-stage boost combustion unit for further pressurization and combustion. While the airflow flows smoothly, the main part centrifugal impeller and the main part turbine are ensured; the axial connection of the secondary boost unit turbine of the secondary boost unit centrifugal impeller is ensured, so that the high energy generated by the gas impacts the turbine blades, and drives the turbine blades to drive the centrifugal compressor to rotate through the rotor shaft. The gas compressed by the three-stage centrifugal compressor has a high pressure ratio and high density, providing a high-pressure environment for the fuel, greatly enhancing the combustion efficiency, improving the thermal efficiency of the fuel, and reducing energy consumption.

[0007] The present invention is achieved through the following technical solutions.

[0008] An ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine, comprising a main body, a two-stage supercharging unit, a three-stage supercharging combustion unit, and a scroll structure connecting pipeline system; the scroll structure connecting pipeline system comprises a scroll structure connecting pipeline 1, a scroll structure connecting pipeline 2, a scroll structure connecting pipeline 3, and a scroll structure connecting pipeline 4;

[0009] The main body part includes a main body air intake part, a main body single-stage centrifugal compressor, a main body single-stage mixed flow turbine, a main body shafting structure, and a tail nozzle. The air intake end of the main body single-stage centrifugal compressor is connected to the main body air intake part. The main body single-stage centrifugal compressor and the main body single-stage mixed flow turbine are coaxially connected through the main body shafting structure. The tail nozzle is connected to the main body single-stage mixed flow turbine. The main body single-stage centrifugal compressor includes a first volute-shaped collector. The first volute-shaped collector is located at the outlet end of the main body single-stage centrifugal compressor. The first volute-shaped collector gradually increases in radius along the gas flow direction to fully collect gas. After collecting gas, the first volute-shaped collector is connected to one end of the scroll structure connecting pipe.

[0010] The secondary boost unit includes an air intake portion of the secondary boost unit, a single-stage centrifugal compressor of the secondary boost unit, a single-stage mixed-flow turbine of the secondary boost unit, and a shaft system structure of the secondary boost unit. The air intake portion of the secondary boost unit is connected to the other end of the scroll structure connecting pipe one, and the gas compressed once by the centrifugal compressor of the main part is transferred to the air intake portion of the secondary boost unit. The air intake end of the single-stage centrifugal compressor of the secondary boost unit is connected to the air intake portion of the secondary boost unit and the gas is compressed for the second time. The single-stage centrifugal compressor of the secondary boost unit and the single-stage mixed-flow turbine of the secondary boost unit are coaxially connected through the shaft system structure of the secondary boost unit. The single-stage centrifugal compressor of the secondary boost unit includes a second volute-shaped collector, which is the outlet end of the single-stage centrifugal compressor of the secondary boost unit. The second volute-shaped collector gradually increases in radius along the gas flow direction to fully collect gas. After collecting gas, the second volute-shaped collector is connected to one end of the scroll structure connecting pipe three;

[0011] The three-stage supercharged combustion unit includes an air intake part of the three-stage supercharged combustion unit, a single-stage centrifugal compressor of the three-stage supercharged combustion unit, a single-stage mixed-flow turbine of the three-stage supercharged combustion unit, a shaft system structure of the three-stage supercharged combustion unit, and a single annular combustion chamber. The air intake part of the three-stage supercharged combustion unit is connected to the other end of the scroll structure connecting pipe three, and the gas compressed twice by the single-stage centrifugal compressor of the two-stage supercharged combustion unit is transferred to the air intake part of the three-stage supercharged combustion unit. The air intake end of the single-stage centrifugal compressor of the three-stage supercharged combustion unit is connected to the air intake part of the three-stage supercharged combustion unit and compresses the gas three times. The single-stage centrifugal compressor of the three-stage supercharged combustion unit and the three-stage supercharged combustion unit are connected to the air intake part of the three-stage supercharged combustion unit. The single-stage mixed flow turbine of the combustion unit is coaxially connected through the three-stage supercharged combustion unit shaft system structure, the single annular combustion chamber is arranged between the single-stage centrifugal compressor of the three-stage supercharged combustion unit and the single-stage mixed flow turbine of the three-stage supercharged combustion unit, the air outlet end of the single-stage mixed flow turbine of the three-stage supercharged combustion unit is connected to one end of the scroll structure connecting pipe four, the other end of the scroll structure connecting pipe four is connected to the air inlet end of the single-stage mixed flow turbine of the two-stage supercharged unit, the air outlet end of the single-stage mixed flow turbine of the two-stage supercharged unit is connected to one end of the scroll structure connecting pipe two, and the other end of the scroll structure connecting pipe two is connected to the air inlet end of the single-stage mixed flow turbine of the main part;

[0012] The gas passes through the air intake part of the main part, the single-stage centrifugal compressor of the main part, the scroll structure connecting pipe one, the air intake part of the two-stage boosting unit, the single-stage centrifugal compressor of the two-stage boosting unit, the scroll structure connecting pipe three, the air intake part of the three-stage boosting combustion unit, and the single-stage centrifugal compressor of the three-stage boosting combustion unit in sequence. The gas after three compressions enters the single annular combustion chamber to participate in combustion. The gas after combustion in the single annular combustion chamber passes through the single-stage mixed flow turbine of the three-stage boosting combustion unit, the scroll structure connecting pipe four, the single-stage mixed flow turbine of the two-stage boosting unit, the scroll structure connecting pipe two, and the single-stage mixed flow turbine of the main part in sequence, and is then discharged through the tail nozzle.

[0013] Furthermore, the air intake portion of the main body comprises a first air intake duct outer cover and a first air intake duct, and the first air intake duct outer cover is connected to the first air intake duct by means of mutually matching card slots and card blocks;

[0014] The main body of the single-stage centrifugal compressor also includes a first single-stage centrifugal impeller, a first diffuser end cover, and a first diffuser. The radial outer side of the first diffuser end cover is connected to the first air inlet outer cover by mutually matching slots and blocks, one side of the first diffuser end cover is connected to the first diffuser by a flange, and the other side of the first diffuser end cover is connected to the first air inlet by a flange. The side of the first volute-shaped collector close to the air inlet direction is connected to the first diffuser end cover by setting mutually matching slots and blocks, and the side of the first volute-shaped collector close to the air outlet direction is connected to the first diffuser by a flange.

[0015] Furthermore, the main body shaft system structure includes a first shaft body, a first shaft sleeve, and a first shaft sleeve component. The first shaft sleeve and the first shaft sleeve component are connected by interference fit. The first single-stage centrifugal impeller is connected to the first shaft body by interference fit through a center hole. The first diffuser is connected to the first shaft sleeve by a flange.

[0016] Furthermore, the main body of the single-stage mixed flow turbine includes a first volute-shaped inlet duct, a first turbine guide, a first single mixed flow turbine blade, a first turbine retaining ring, and a first turbine fixing nut. The first turbine guide is connected to the first sleeve component by an interference fit, the first single mixed flow turbine blade is connected to the first shaft body, the center hole of the first single mixed flow turbine blade is matched with the first shaft body, the first turbine retaining ring is interference fit with the first shaft body, and is placed on the front side of the first single mixed flow turbine blade in the intake direction through the first shaft body, the first turbine fixing nut is interference fit with the first shaft body, and is placed on the rear side of the first single mixed flow turbine blade in the near direction through the first shaft body, thereby fixing the first single mixed flow turbine blade, and the tail nozzle is connected to the first turbine guide by a flange.

[0017] Furthermore, the air intake portion of the secondary supercharging unit includes a second air intake duct outer cover and a second air intake duct, and the second air intake duct outer cover is connected to the second air intake duct by means of mutually matching card slots and card blocks;

[0018] The single-stage centrifugal compressor of the two-stage boost unit includes a second single-stage centrifugal impeller, a second diffuser end cover, a second diffuser, and a second volute-shaped collector. The radial outer side of the second diffuser end cover is connected to the second air inlet duct outer cover by mutually matching slots and blocks, one side of the second diffuser end cover is connected to the second diffuser by a flange, and the other side of the second diffuser end cover is connected to the second air inlet duct by a flange. The side of the second volute-shaped collector close to the air inlet direction is connected to the second diffuser end cover by setting mutually matching slots and blocks, and the side of the second volute-shaped collector close to the air outlet direction is connected to the second diffuser by a flange.

[0019] Furthermore, the secondary boost unit shaft system structure includes a second shaft body, a second shaft sleeve, and a second shaft sleeve component. The second shaft sleeve and the second shaft sleeve component are connected by interference fit. The second single-stage centrifugal impeller is connected to the second shaft body by interference fit through a center hole, and the second diffuser is connected to the second shaft sleeve by a flange.

[0020] Furthermore, the single-stage mixed flow turbine of the two-stage supercharging unit includes a second volute-shaped inlet duct, a second turbine guide, a second single mixed flow turbine blade, a second turbine retaining ring, and a second turbine fixing nut. The second turbine guide is connected to the second sleeve component by an interference fit, the second single mixed flow turbine blade is connected to the second shaft body, the center hole of the second single mixed flow turbine blade is matched with the second shaft body, the second turbine retaining ring is interference fit with the second shaft body, and is placed on the front side of the second single mixed flow turbine blade in the intake direction through the second shaft body, the second turbine fixing nut is interference fit with the second shaft body, and is placed on the rear side of the second single mixed flow turbine blade in the near direction through the second shaft body, thereby fixing the second single mixed flow turbine blade, after the airflow flows out through the second single mixed flow turbine blade, it flows through the second airflow guide device and connects the pipeline through the scroll structure to the first volute-shaped inlet duct, further driving the first single mixed flow turbine blade of the main part to rotate, generating thrust, and ejecting from the tail nozzle.

[0021] Furthermore, the air intake part of the three-stage supercharging combustion unit includes a third air intake passage, which is connected to the scroll structure connecting pipe three, and the gas pressurized by the second-stage supercharging unit enters the third air intake passage of the three-stage supercharging combustion unit along the scroll structure connecting pipe three, and the three-stage supercharging starts;

[0022] The three-stage supercharging combustion unit single-stage centrifugal compressor comprises a third single-stage centrifugal impeller, a third diffuser, and a single-stage centrifugal compressor casing, the third air inlet is connected to the single-stage centrifugal compressor casing, the third single-stage centrifugal impeller is connected to the third shaft body through an interference fit through a center hole, and the third diffuser is connected to the third sleeve through a flange;

[0023] The three-stage supercharged combustion unit shaft system structure includes a third shaft body, a third shaft sleeve, and a third shaft sleeve component. The third shaft sleeve and the third shaft sleeve component are connected by interference fit.

[0024] Furthermore, the single annular combustion chamber includes a combustion chamber casing, an annular combustion chamber, and a fuel nozzle. The single-stage centrifugal compressor casing is tightly connected to the combustion chamber casing, the annular combustion chamber is tightly coupled to the third turbine guide vane, and the fuel nozzle is arranged on the annular combustion chamber.

[0025] Further, the three-stage supercharged combustion unit single-stage mixed flow turbine includes a third turbine guide, a third single mixed flow turbine blade, a third turbine retaining ring, and a third turbine fixing nut. The third turbine guide is connected to the third shaft sleeve component by interference fit, the third single mixed flow turbine blade is connected to the third shaft body, the third single mixed flow turbine blade center hole is matched with the third shaft body, the third turbine retaining ring is interference fit with the third shaft body, and is placed on the front side of the third single mixed flow turbine blade in the intake direction through the third shaft body, the third turbine fixing nut is interference fit with the third shaft body, and is placed on the rear side of the third single mixed flow turbine blade in the near direction through the third shaft body, thereby fixing the third single mixed flow turbine blade;

[0026] After the airflow flows out through the third single mixed flow turbine blade, it flows through the third airflow guide device to change the gas flow direction. The gas flows to the second volute-shaped air inlet duct through the scroll structure connecting pipe four, further driving the second single mixed flow turbine blade of the secondary supercharging unit to rotate, generating thrust.

[0027] Compared with the prior art, the advantages of the present invention are:

[0028] 1. With the increase of the boost ratio, the gas after combustion expands in the turbine and does work more fully, more effectively converting the heat energy generated by the combustion of the fuel into mechanical energy, greatly improving the thermal efficiency of the fuel, improving fuel economy, and significantly reducing fuel consumption;

[0029] 2. The three-stage centrifugal supercharged combustion based on the centrifugal compressor is adopted, and the overall gas pressure and density are greatly improved. The compression ratio exceeds 100, providing a high-pressure environment for the fuel, which will significantly improve the thrust performance of the engine;

[0030] 3. The three-stage turbine structure is adopted. The high-temperature and high-pressure gas after combustion in the combustion chamber has high internal energy. After passing through the three-stage turbine, the three-stage turbine is fully driven to rotate and do work, and the energy in the gas is fully converted into mechanical work, thereby effectively improving the power output efficiency of the entire power device;

[0031] 4. Based on the three-stage turbine design, the engine load is effectively dispersed to improve reliability. By setting up a three-stage turbine to gradually absorb the energy, compared with a single-stage turbine that bears all the energy to do work, it can better disperse the mechanical load, avoid the single-stage turbine from being subjected to excessive stress and torque, reduce the possibility and risk of local excessive fatigue and damage, and improve the overall reliability of the system;

[0032] 5. Compared with multi-stage axial flow compressors with the same or even lower compression ratio, there are only three-stage compressors with fewer components. The axial length between the compressor and the turbine is greatly reduced, making the engine structure simple and compact, effectively reducing the engine weight to obtain better flight performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a stereoscopic view of the overall appearance of the engine structure of the present invention;

[0034] Figure 2 It is a schematic cross-sectional view of the overall structure of the engine of the present invention;

[0035] Figure 3 It is a schematic cross-sectional view of the structure of the main part of the present invention;

[0036] Figure 4 It is a schematic cross-sectional view of the structure of the two-stage boosting unit of the present invention;

[0037] Figure 5 It is a schematic cross-sectional view of the structure of the three-stage supercharged combustion unit of the present invention;

[0038] Figure 6 This is a schematic diagram of the reel structure connected to the pipeline structure of the present invention;

[0039] Figure 7 It is a schematic diagram of gas flow of the present invention;

[0040] In the figure, 1. main part, 2. secondary pressurization unit, 3. tertiary pressurization combustion unit, 4. scroll structure connecting pipeline system.

[0041] 11. Air intake part of the main part, 12. Single-stage centrifugal compressor of the main part, 13. Single-stage mixed flow turbine of the main part, 14. Shaft system structure of the main part, 15. Tail nozzle;

[0042] 21. Air intake part of the two-stage supercharging unit, 22. Single-stage centrifugal compressor of the two-stage supercharging unit, 23. Single-stage mixed flow turbine of the two-stage supercharging unit, 24. Shaft system structure of the two-stage supercharging unit;

[0043] 31. Intake part of three-stage supercharged combustion unit, 32. Single-stage centrifugal compressor of three-stage supercharged combustion unit, 33. Single-stage mixed flow turbine of three-stage supercharged combustion unit, 34. Shafting structure of three-stage supercharged combustion unit, 36. Single annular combustion chamber of three-stage supercharged combustion unit;

[0044] 41. The reel structure is connected to pipeline one. 42. The reel structure is connected to pipeline two. 43. The reel structure is connected to pipeline three. 44. The reel structure is connected to pipeline four. DETAILED DESCRIPTION

[0045] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0046] A compact, energy-efficient, ultra-high-pressure ratio turbojet engine mainly includes a main body, a two-stage centrifugal supercharging unit, a three-stage centrifugal supercharging combustion unit, and a scroll structure connecting pipeline system. The two-stage centrifugal supercharging unit is arranged axially vertically with the main body, and the three-stage centrifugal supercharging unit is arranged vertically with the two-stage centrifugal supercharging unit, and they are respectively connected by scroll structure connecting pipelines. The gas entering the engine is subjected to three-stage supercharging in the above manner. After the three-stage supercharging, the gas is fully mixed with the fuel in the single annular combustion chamber in the three-stage centrifugal supercharging combustion unit and burns to produce high-temperature, high-pressure combustion gas, which drives the three-stage turbine to rotate at high speed, and continues to flow to the two-stage turbine and the first-stage turbine through the scroll-shaped fixed connecting pipeline on the rear side, and is ejected from the tail nozzle to generate huge thrust.

[0047] The main part of the turbojet engine is characterized by comprising a main part air inlet, a main part centrifugal compressor, a main part single mixed flow turbine, and a tail nozzle.

[0048] The connection part between the main body of the turbojet engine and the secondary supercharging unit is characterized in that the air intake pipe and the exhaust pipe of the secondary supercharging unit are connected to the air outlet part of the compressor of the main body and the air intake part of the turbine through two reel structure connecting pipes respectively. It is divided into front and rear end connections, characterized in that the front end connection mode is that one end of the reel structure connecting pipe is connected to the manifold of the first-stage centrifugal compressor in the main body, and the other end is connected to the air intake duct of the second-stage centrifuge in the second-stage centrifugal supercharging unit; the rear end connection mode is that one end of the reel-shaped fixed connecting pipe is connected to the outlet of the second-stage turbine in the second-stage centrifugal supercharging unit, and the other end is connected to the air intake end of the first-stage turbine of the main body.

[0049] The two-stage centrifugal supercharging unit includes a single centrifugal compressor of the two-stage centrifugal supercharging unit and a single mixed flow turbine of the two-stage centrifugal supercharging unit. The two-stage supercharging unit is connected to the primary centrifuge and the turbine inter-region of the main part through a scroll structure pipeline, and is placed vertically to the axial direction of the main part.

[0050] The connection part between the second-stage centrifugal supercharging unit and the third-stage centrifugal supercharging combustion unit of the turbojet engine is characterized in that the third-stage supercharging combustion unit is connected to the area between the second-stage centrifuge and the second-stage turbine of the second-stage supercharging unit through a scroll structure pipeline, and is placed axially perpendicular to the second-stage supercharging unit.

[0051] The three-stage supercharged combustion unit includes a three-stage supercharged combustion unit single-stage centrifugal compressor, a single annular combustion chamber, a three-stage supercharged combustion unit single mixed flow turbine, and is provided with a fuel nozzle. It is connected to the two-stage supercharged unit through a scroll structure pipeline and is placed axially vertically.

[0052] The three-stage supercharging and combustion unit is provided with a single annular combustion chamber and a fuel nozzle. After the airflow passes through the single-stage centrifugal compressor of the main part and the single-stage centrifugal compressor of the secondary centrifugal supercharging unit, it enters the three-stage supercharging and combustion unit through the scroll-shaped pipeline for three times of centrifugal supercharging. The gas that has passed the three-stage supercharging is fully mixed with the fuel in the single annular combustion chamber and burns to produce high-temperature and high-pressure combustion gas, which drives the three-stage turbine to rotate at high speed.

[0053] By redesigning the turbojet engine structure, three-stage gas compression is achieved.

[0054] The following is a detailed introduction to the specific structure of an ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine of the present invention.

[0055] like Figure 1 As shown, an ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine includes a main body, a two-stage supercharging unit, a three-stage supercharging combustion unit, and a scroll structure connecting pipeline system.

[0056] 1.1 Main part

[0057] like Figure 3 As shown, the main body (1) includes a main body air intake (11), a main body single-stage centrifugal compressor (12), a main body single-stage mixed flow turbine (13), a main body shaft system structure (14), and a tail nozzle (15).

[0058] The main body air intake part (11) comprises a first air intake duct outer cover (111) and a first air intake duct (112). The first air intake duct outer cover (111) and the first air intake duct (112) are connected by means of mutually matching card slots and card blocks.

[0059] The main body of the single-stage centrifugal compressor (12) comprises a first single-stage centrifugal impeller (121), a first diffuser end cover (122), a first diffuser (123), and a first volute-shaped header (124). The radial outer side of the first diffuser end cover (122) is connected to the first air inlet cover (111) through mutually matching card slots and card blocks, and the first diffuser end cover (122) and the first diffuser (123) are connected through flanges. The first diffuser end cover (122) is provided with a flange, and bolt holes are correspondingly provided on the flange of the first diffuser end cover (122). The diffuser stator blades are provided with bolt holes corresponding to those on the flange of the first diffuser end cover (122), and the two bolt holes overlap and are connected by bolts. The first diffuser end cover (122) is connected to the first air inlet (112) via a flange, and the first air inlet (112) is provided with bolt holes corresponding to the flange plate of the first diffuser end cover (122), and the two bolt holes overlap and are connected via bolts.

[0060] The first volute-shaped collecting pipe (124) is connected to the first diffuser end cover (122) and the first diffuser (123). The first volute-shaped collecting pipe (124) and the first diffuser end cover (122) are connected by setting mutually matching card slots and card blocks. The card block is set on the side of the first volute-shaped swirler (124) close to the air inlet direction, and the card slot is set on the radial outer side of the first diffuser end cover (122), and they are matched and connected. The first volute-shaped collecting pipe (124) and the first diffuser (123) are connected by a flange. The side of the first volute-shaped collecting pipe (124) close to the air outlet direction is provided with a bolt hole corresponding to the flange of the first diffuser (123), and they are connected by bolts. The radius of the first volute-shaped collecting pipe (124) increases with the flow direction of the gas, so as to fully collect the gas. After collecting the gas for one cycle, the first volute-shaped collecting pipe (124) is connected to the scroll structure connecting pipe one (41), and the gas compressed once by the centrifugal compressor (12) of the main part (1) is transferred to the secondary boosting unit intake part (21) of the secondary boosting unit (2) through the scroll structure connecting pipe one (41) for secondary compression.

[0061] The main body shaft system structure (14) includes a first shaft body (141), a first shaft sleeve (142), and a first shaft sleeve component (143). The first shaft sleeve (142) and the first shaft sleeve component (143) are connected by interference fit. The first shaft body (141) is connected to other components through the first shaft sleeve (142). The first single-stage centrifugal impeller (121) is connected to the first shaft body (141) through an interference fit through a center hole. The first diffuser (123) is connected to the first shaft sleeve (142) by a flange, a flange is provided on the first diffuser (123) plate, bolt holes are provided on the first diffuser (123) flange, and bolt holes corresponding to the first diffuser (123) flange are provided on the first shaft sleeve (142), and the two bolt holes are connected by bolts.

[0062] The main body single-stage mixed flow turbine (13) comprises a first volute-shaped air inlet (131), a first turbine guide (132), a first single mixed flow turbine blade (133), a first turbine retaining ring (134), and a first turbine fixing nut (135). The first turbine guide (132) is connected to the first sleeve component (143) by interference fit. The first single mixed flow turbine blade (133) is connected to the first shaft body (141), the center hole of the first single mixed flow turbine blade (133) is matched with the first shaft body (141), the first turbine retaining ring (134) is interference fit with the first shaft body (141), and is placed on the front side of the first single mixed flow turbine blade (133) in the air inlet direction through the first shaft body (141), and the first turbine fixing nut (135) is interference fit with the first shaft body (141), and is placed on the rear side of the first single mixed flow turbine blade (133) in the near direction through the first shaft body (141), thereby fixing the first single mixed flow turbine blade (133). The tail nozzle (15) and the first turbine guide (132) are connected by flanges. The radial outer end of the first turbine guide (132) is provided with a flange plate with bolt holes. The tail nozzle (15) flange plate is connected by bolts through corresponding bolt holes.

[0063] The first single-stage centrifugal impeller (121) is connected to the first single-stage mixed-flow turbine blade (133) via the main body shaft system structure (14), thereby achieving power transmission and coordinated work between components.

[0064] 1.2 Two-stage booster unit

[0065] like Figure 4 As shown, the two-stage boost unit (2) includes a two-stage boost unit air intake part (21), a two-stage boost unit single-stage centrifugal compressor (22), a two-stage boost unit single-stage mixed flow turbine (23), and a two-stage boost unit shaft system structure (24).

[0066] The secondary supercharging unit air intake part (21) comprises a second air intake duct outer cover (211) and a second air intake duct (212). The second air intake duct outer cover (211) and the second air intake duct (212) are connected by means of mutually matching card slots and card blocks.

[0067] The two-stage boost unit single-stage centrifugal compressor (22) comprises a second single-stage centrifugal impeller (221), a second diffuser end cover (222), a second diffuser (223), and a second volute-shaped header (224). The radial outer side of the second diffuser end cover (222) is connected to the second air inlet duct outer cover (211) through mutually matching card slots and card blocks, and the second diffuser end cover (222) and the second diffuser (223) are connected through flanges. The second diffuser end cover (222) is provided with a flange, and bolt holes are correspondingly provided on the flange of the second diffuser end cover (222). The diffuser stator blades are provided with bolt holes corresponding to the bolt holes on the flange of the second diffuser end cover (222), and the two bolt holes overlap and are connected by bolts. The second diffuser end cover (222) is connected to the second air inlet (212) via a flange, and the second air inlet (212) is provided with bolt holes corresponding to the flange plate of the second diffuser end cover (222), and the two bolt holes overlap and are connected via bolts.

[0068] The second volute-shaped collecting pipe (224) is connected to the second diffuser end cover (222) and the second diffuser (223). The second volute-shaped collecting pipe (224) and the second diffuser end cover (222) are connected by setting mutually matching card slots and card blocks. The card block is set on the side of the second volute-shaped collecting pipe (224) close to the air inlet direction, and the card slot is set on the radial outer side of the second diffuser end cover (222), and they are matched and connected. The second volute-shaped collecting pipe (224) and the second diffuser (223) are connected by a flange. The side of the second volute-shaped collecting pipe (224) close to the air outlet direction is provided with bolt holes corresponding to the flange of the second diffuser (223), and they are connected by bolts. The radius of the second volute-shaped collecting pipe (224) increases with the flow direction of the gas, so as to fully collect the gas. After collecting the gas for one cycle, the second volute-shaped collecting pipe (224) is connected to the scroll structure connecting pipe three (43), and the gas compressed twice by the centrifugal compressor (22) of the secondary boosting unit (2) is transferred to the third-stage boosting combustion unit (3) of the third-stage boosting combustion unit intake part (31) through the scroll structure connecting pipe three (43) for three-stage compression.

[0069] The secondary boost unit shaft system structure (24) includes a second shaft body (241), a second shaft sleeve (242), and a second shaft sleeve component (243). The second shaft sleeve (242) and the second shaft sleeve component (243) are connected by interference fit. The second shaft body (241) is connected to other components through the second shaft sleeve (242). The second single-stage centrifugal impeller (221) is connected to the second shaft body (241) through an interference fit through a center hole. The second diffuser (223) is connected to the second shaft sleeve (242) by a flange, a flange is provided on the second diffuser (223) plate, bolt holes are provided on the second diffuser (223) flange, and bolt holes corresponding to the second diffuser (223) flange are provided on the second shaft sleeve (242), and the two bolt holes are connected by bolts.

[0070] The two-stage supercharging unit single-stage mixed flow turbine (23) comprises a second volute-shaped air inlet (231), a second turbine guide (232), a second single mixed flow turbine blade (233), a second turbine retaining ring (234), and a second turbine fixing nut (235). The second turbine guide (232) is connected to the second shaft sleeve component (243) by interference fit. The second single mixed flow turbine blade (233) is connected to the second shaft (241), the center hole of the second single mixed flow turbine blade (233) is matched with the second shaft (241), the second turbine retaining ring (234) is interference fit with the second shaft (241), and is placed on the front side of the second single mixed flow turbine blade (233) in the intake direction through the second shaft (241), the second turbine fixing nut (235) is interference fit with the second shaft (241), and is placed on the rear side of the second single mixed flow turbine blade (233) in the near direction through the second shaft (241), thereby fixing the second single mixed flow turbine blade (233). After the airflow flows out through the second single mixed flow turbine blade (233), it flows through the second airflow guide device (236) and flows to the first volute-shaped air inlet (131) of the main part (1) through the scroll structure connecting pipe 2 (42), further driving the first single mixed flow turbine blade (133) of the main part (1) to rotate, generating thrust, and ejecting from the tail nozzle (15).

[0071] The second single-stage centrifugal impeller (221) is connected to the second single-stage mixed-flow turbine blade (233) via the secondary supercharging unit shaft system structure (24), thereby achieving power transmission and coordinated work between components.

[0072] 1.3 Three-stage boost combustion unit

[0073] like Figure 3 As shown, the three-stage supercharged combustion unit (3) includes a three-stage supercharged combustion unit air intake portion (31), a three-stage supercharged combustion unit single-stage centrifugal compressor (32), a three-stage supercharged combustion unit single-stage mixed flow turbine (33), a three-stage supercharged combustion unit shaft system structure (34), and a single annular combustion chamber (36).

[0074] The air intake part (31) of the three-stage supercharging combustion unit includes a third air intake passage (312). The third air intake passage (312) is connected to the scroll structure connecting pipe three (43), and the gas pressurized by the two-stage supercharging unit enters the third air intake passage (312) of the three-stage supercharging combustion unit (3) along the scroll structure connecting pipe three (43), and the three-stage supercharging begins.

[0075] The three-stage supercharged combustion unit single-stage centrifugal compressor (32) includes a third single-stage centrifugal impeller (321), a third diffuser (323), and a single-stage centrifugal compressor casing (325). The third air inlet (312) is connected to the single-stage centrifugal compressor casing (325) by welding. The third single-stage centrifugal impeller (321) is connected to the third shaft body (341) through an interference fit through a center hole. The third diffuser (323) is connected to the third shaft sleeve (342) through a flange, and a flange is provided on the third diffuser (323) plate. Bolt holes are provided on the third diffuser (323) flange, and bolt holes corresponding to the third diffuser (323) flange are provided on the third shaft sleeve (342), and the two bolt holes are connected by bolts.

[0076] The three-stage supercharged combustion unit shaft system structure (34) comprises a third shaft body (341), a third shaft sleeve (342), and a third shaft sleeve component (343). The third shaft sleeve (342) and the third shaft sleeve component (343) are connected by interference fit. The third shaft body (341) is connected to other components through the third shaft sleeve (342).

[0077] The single annular combustion chamber (36) comprises a combustion chamber casing (361), an annular combustion chamber (362), and a fuel nozzle (363). The single-stage centrifugal compressor casing (325) and the combustion chamber casing (361) are tightly connected by welding. The annular combustion chamber (362) is tightly coupled with the third turbine guide vane (332), and the fuel nozzle (363) is arranged on the annular combustion chamber (362).

[0078] The three-stage supercharged combustion unit single-stage mixed flow turbine (33) comprises a third turbine guide (332), a third single mixed flow turbine blade (333), a third turbine retaining ring (334), and a third turbine fixing nut (335). The third turbine guide (332) is connected to the third sleeve component (343) by interference fit. The third single mixed flow turbine blade (333) is connected to the third shaft body (341), the center hole of the third single mixed flow turbine blade (333) is matched with the third shaft body (341), the third turbine retaining ring (334) is interference fit with the third shaft body (341), and is placed on the front side of the third single mixed flow turbine blade (333) in the intake direction through the third shaft body (341), and the third turbine fixing nut (335) is interference fit with the third shaft body (341), and is placed on the rear side of the third single mixed flow turbine blade (333) in the near direction through the third shaft body (341), thereby fixing the third single mixed flow turbine blade (333).

[0079] After the airflow flows out through the third single mixed flow turbine blade (333), it flows through the third airflow guide device (336) to change the direction of gas flow. The gas flows to the second volute-shaped air inlet (231) of the secondary supercharging unit (2) through the scroll structure connecting pipe four (44), further driving the second single mixed flow turbine blade (233) of the secondary supercharging unit (2) to rotate, thereby generating thrust.

[0080] The third single-stage centrifugal impeller (321) is connected to the third single-stage mixed-flow turbine blade (333) via the three-stage supercharging combustion unit shaft system structure (34), thereby achieving power transmission and coordinated work between components.

[0081] 1.4 Reel structure connecting piping system

[0082] according to Figure 6 As shown, the various parts of the present invention are connected by reel structure connecting pipes, and the reel structure connecting pipe system (4) mainly includes four connecting pipes, namely reel structure connecting pipe 1 (41), reel structure connecting pipe 2 (42), reel structure connecting pipe 3 (43), and reel structure connecting pipe 4 (44).

[0083] The scroll structure connecting pipe 1 (41) connects the volute-shaped manifold (124) in the main body (1) main body single-stage centrifugal compressor (12) and the second air inlet (212) of the secondary boosting unit (2), and is responsible for introducing the gas compressed by the primary stage of the main body (1) main body single-stage centrifugal compressor (12) into the secondary boosting unit (2) secondary boosting unit single-stage centrifugal compressor (22) for secondary boosting;

[0084] The scroll structure connecting pipe three (43) is connected to the second volute-shaped manifold (224) in the single-stage centrifugal compressor (22) of the secondary supercharging unit (2) and the third air inlet (312) of the secondary supercharging unit (3), and is responsible for introducing the gas compressed by the secondary supercharging unit (2) of the single-stage centrifugal compressor (22) of the secondary supercharging unit (2) into the single-stage centrifugal compressor (32) of the three-stage supercharging combustion unit (3) for three-stage supercharging and subsequent combustion;

[0085] The scroll structure connecting pipe four (44) is connected to the second volute-shaped air inlet (231) of the second-stage supercharging unit (2) and the airflow outlet end of the turbine trailing edge of the third-stage supercharging combustion unit (3), and is responsible for introducing the gas that has undergone the third-stage supercharging and the energy conversion through the first-stage turbine into the second-stage supercharging unit (2) and the single mixed flow turbine (23) of the second-stage supercharging unit for secondary energy conversion, thereby driving the single mixed flow turbine blades (233) of the second-stage supercharging unit to rotate;

[0086] The scroll structure connecting pipe 2 (42) is connected to the first volute-shaped air inlet (131) of the main part (1) main part single mixed flow turbine (13) and the air flow outlet end of the turbine trailing edge of the secondary supercharging unit (2), and is responsible for introducing the gas that has undergone three-stage supercharging and energy conversion through the secondary turbine into the main part (1) main part single mixed flow turbine (13) for three-stage energy conversion, driving the main part single mixed flow turbine blades (133) to rotate to generate thrust, and ejecting it from the tail nozzle (15).

[0087] 2.1 Airflow Direction Description

[0088] according to Figure 7As shown, the gas flow direction of the present invention is as follows. The air in the environment enters the main part air inlet (112) and enters the main part (1) main part single-stage centrifugal compressor (12) for primary supercharging, and is connected to the scroll structure connecting pipe one (41) through the first volute-shaped manifold (124) to introduce the gas after primary supercharging into the secondary supercharging unit (2) for secondary centrifugal supercharging. The gas enters the secondary supercharging unit air inlet (212) of the secondary supercharging unit (2), and is secondary supercharging in the secondary supercharging unit (2) secondary supercharging unit single-stage centrifugal compressor (22), and is connected to the scroll structure connecting pipe three (43) through the second volute-shaped manifold (224) to introduce the gas after secondary supercharging into the third-stage supercharging combustion unit (3) for third-stage centrifugal supercharging and combustion. The gas enters the three-stage supercharging combustion unit (3) and the three-stage supercharging combustion unit inlet duct (312), undergoes three-stage supercharging in the three-stage supercharging combustion unit single-stage centrifugal compressor (32), and enters the single annular combustion chamber (36) for full combustion. The combusted gas enters the three-stage supercharging combustion unit single-stage mixed flow turbine (33) for primary energy conversion, driving the third single-stage mixed flow turbine blade (333) to rotate. The gas enters the two-stage supercharging unit (2) and the two-stage supercharging unit single mixed flow turbine (23) through the scroll structure connecting pipeline four (44) for secondary energy conversion, driving the second single-stage mixed flow turbine blade (233) to rotate. The gas enters the main body (1) and the main body single mixed flow turbine (13) through the scroll structure connecting pipeline two (42) for three-stage energy conversion, driving the first single-stage mixed flow turbine blade (133) to rotate, generating thrust and ejecting from the tail nozzle (15).

[0089] 3.1 Working principle:

[0090] Starting process: The engine rotor is driven to rotate by a gas turbine starter motor (not shown in the figure), and the engine speed begins to rise. When the speed gradually rises to the minimum starting speed for engine ignition, the fuel system fuel nozzle (363) begins to spray fuel into the annular combustion chamber (362). At the same time, the igniter (not shown in the figure) generates high-temperature sparks in the annular combustion chamber (362), and the fuel system begins to spray fuel. The atomized fuel is mixed with air and ignited to form a stable combustion and ignite the mixed gas. The three-stage supercharged combustion unit single-stage mixed flow turbine (33) begins to generate power and drives the second single-stage mixed flow turbine blade (233) to rotate. The gas passes through the second single-stage mixed flow turbine blade (233) to continuously drive the first single-stage mixed flow turbine blade (133) to rotate. At this time, the gas turbine starter motor continues to provide power. When the power provided by the turbine is sufficient to replace the power of the gas turbine starter motor, the gas turbine starter motor is disconnected from the engine. After the gas turbine starter motor helps the engine to quickly accelerate to a self-acceleration state, the engine enters an autonomous operation state.

[0091] Stable operation stage: The main part single-stage centrifugal compressor (12) sucks in and compresses the outside air to increase the pressure and temperature of the air. The centrifugal compressor uses centrifugal force to accelerate the air and throw it to the outer edge of the impeller, thereby achieving air supercharging. The gas that has been supercharged once is sent to the two-stage supercharging unit single-stage centrifugal compressor (22) for secondary supercharging. The gas that has been supercharged twice is sent to the three-stage supercharging unit single-stage centrifugal compressor (32) for tertiary supercharging, and then enters the annular combustion chamber (362). In the annular combustion chamber (362), the compressed air is mixed with the fuel and then burned, converting the chemical energy of the fuel into heat energy and generating high-temperature and high-pressure gas. The high-temperature and high-pressure gas drives the turbine to rotate and expands in the turbine. The turbine and the compressor are connected by a shaft. The rotation of the turbine drives the compressor to continue to compress the intake air, forming a continuous working cycle to maintain the operation of the compressor. After passing through the turbine, the combustion gas still has relatively high energy, and then enters the tail nozzle (15) to continue to expand and accelerate, after which the gas is discharged from the tail nozzle (15) at high speed, generating thrust.

[0092] Shutdown process: Slowly shut down the fuel supply, gradually reduce the fuel and cut it off. In the annular combustion chamber (362), the combustion process gradually stops, and the generation of gas also stops. After the fuel is cut off, the engine rotor gradually slows down due to inertia and air resistance because there is no fuel to push it. The engine rotor continues to rotate for a period of time due to inertia and finally stops.

[0093] 4.1 Energy consumption reduction effect:

[0094] Thermal efficiency improvement:

[0095] The working thermal cycle of a turbojet engine follows the Brayton cycle. The thermal efficiency formula of the Brayton cycle is as follows:

[0096]

[0097] Among them, π is the cycle pressure ratio, k is the adiabatic index (specific heat ratio) of the working fluid. Here, air can be approximated as an ideal gas, and its k value is usually around 1.4.

[0098] The pressure ratio of a small turbojet engine with good performance using a single-stage centrifugal compressor is π6, and the thermal efficiency of the Brayton cycle under single-stage centrifugal compressor is η t0 40.07%;

[0099] The invention discloses an ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine. After three-stage supercharging, the supercharging ratio π can reach 3×2×1.5=9. The calculated Brayton cycle thermal efficiency η under three-stage supercharging is t1 46.62%;

[0100] Thermal efficiency improvement Δη t =ηt1 -η t0 =6.52%.

[0101] Reduction in fuel consumption:

[0102] The fuel consumption rate sfc is defined as the amount of fuel consumed to produce 1N (or 1daN) thrust per second, and its unit is kg / (N·h).

[0103] It is an indicator of the engine's economic performance at a certain flight speed.

[0104]

[0105] Among them, q mf is the fuel flow of the engine, in kg / s, F is the thrust of the engine, in N;

[0106] For a small turbojet engine with a single-stage centrifugal compressor, its fuel consumption rate sfc0≈1.3624kg / (daN·h);

[0107] For the ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine of the present invention, its fuel consumption rate sfc1≈1.0994kg / (daN·h);

[0108] Reduced fuel consumption

[0109] The above description is only a preferred embodiment of the present invention, and does not limit the implementation mode and protection scope of the present invention. For those skilled in the art, it should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. An ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine, characterized in that: The invention comprises a main body (1), a secondary pressure-boosting unit (2), a tertiary pressure-boosting combustion unit (3), and a reel structure connecting pipeline system (4); the reel structure connecting pipeline system (4) comprises a reel structure connecting pipeline 1 (41), a reel structure connecting pipeline 2 (42), a reel structure connecting pipeline 3 (43), and a reel structure connecting pipeline 4 (44); The main body (1) comprises a main body air intake portion (11), a main body single-stage centrifugal compressor (12), a main body single-stage mixed flow turbine (13), a main body shaft structure (14), and a tail nozzle (15); an air intake end of the main body single-stage centrifugal compressor (12) is connected to the main body air intake portion (11); the main body single-stage centrifugal compressor (12) and the main body single-stage mixed flow turbine (13) are coaxially connected via the main body shaft structure (14); The tail nozzle (15) is connected to the main body single-stage mixed flow turbine (13), and the main body single-stage centrifugal compressor (12) includes a first volute-shaped collecting pipe (124). The first volute-shaped collecting pipe (124) is located at the gas outlet end of the main body single-stage centrifugal compressor (12). The radius of the first volute-shaped collecting pipe (124) gradually increases along the gas flow direction, and the gas is fully collected. After the gas is collected, the first volute-shaped collecting pipe (124) is connected to one end of the scroll structure connecting pipe (41); The secondary boost unit (2) comprises a secondary boost unit air intake portion (21), a secondary boost unit single-stage centrifugal compressor (22), a secondary boost unit single-stage mixed flow turbine (23), and a secondary boost unit shaft system structure (24). The secondary boost unit air intake portion (21) is connected to the other end of the scroll structure connecting pipeline (41) to transfer the gas compressed once by the main body centrifugal compressor (12) to the secondary boost unit air intake portion (21). The air intake end of the secondary boost unit single-stage centrifugal compressor (22) is connected to the secondary boost unit air intake portion (21) and performs secondary compression on the gas. secondary compression, a secondary boost unit single-stage centrifugal compressor (22) and a secondary boost unit single-stage mixed flow turbine (23) are coaxially connected through a secondary boost unit shaft system structure (24), the secondary boost unit single-stage centrifugal compressor (22) comprises a second volute-shaped collecting pipe (224), the second volute-shaped collecting pipe (224) is the gas outlet end of the secondary boost unit single-stage centrifugal compressor (22), the second volute-shaped collecting pipe (224) gradually increases in radius along the gas flow direction, and the gas is fully collected, and after the gas is collected, the second volute-shaped collecting pipe (224) is connected to one end of the scroll structure connecting pipe three (43); The three-stage supercharged combustion unit (3) comprises a three-stage supercharged combustion unit air intake portion (31), a three-stage supercharged combustion unit single-stage centrifugal compressor (32), a three-stage supercharged combustion unit single-stage mixed flow turbine (33), a three-stage supercharged combustion unit shaft system structure (34), and a single annular combustion chamber (36). The three-stage supercharged combustion unit air intake portion (31) is connected to the other end of the scroll structure connecting pipe three (43), and the gas compressed twice by the two-stage supercharged unit single-stage centrifugal compressor (22) is transferred to the three-stage supercharged combustion unit air intake portion (31). The air intake end of the three-stage supercharged combustion unit single-stage centrifugal compressor (32) is connected to the three-stage supercharged combustion unit air intake portion (31) and compresses the gas three times. The three-stage supercharged combustion unit single-stage centrifugal compressor (32) and the three-stage supercharged combustion unit are connected to the three-stage supercharged combustion unit air intake portion (31) and the gas is compressed three times. The combustion unit single-stage mixed flow turbine (33) is coaxially connected through the three-stage supercharging combustion unit shaft system structure (34); the single annular combustion chamber (36) is arranged between the three-stage supercharging combustion unit single-stage centrifugal compressor (32) and the three-stage supercharging combustion unit single-stage mixed flow turbine (33); the air outlet end of the three-stage supercharging combustion unit single-stage mixed flow turbine (33) is connected to one end of the scroll structure connecting pipe four (44); the other end of the scroll structure connecting pipe four (44) is connected to the air inlet end of the two-stage supercharging unit single-stage mixed flow turbine (23); the air outlet end of the two-stage supercharging unit single-stage mixed flow turbine (23) is connected to one end of the scroll structure connecting pipe two (44); the other end of the scroll structure connecting pipe two (44) is connected to the air inlet end of the main body single-stage mixed flow turbine (13); The gas sequentially passes through the air intake portion (11) of the main part, the single-stage centrifugal compressor (12) of the main part, the first scroll structure connecting pipeline (41), the air intake portion (21) of the second-stage supercharging unit, the single-stage centrifugal compressor (22) of the second-stage supercharging unit, the third scroll structure connecting pipeline (43), the air intake portion (31) of the third-stage supercharging combustion unit, and the single-stage centrifugal compressor (32) of the third-stage supercharging combustion unit. After being compressed three times, the gas enters the single-annular combustion chamber (36) to participate in combustion. After combustion in the single-annular combustion chamber (36), the gas sequentially passes through the single-stage mixed flow turbine (33) of the third-stage supercharging combustion unit, the fourth scroll structure connecting pipeline (44), the single-stage mixed flow turbine (23) of the second-stage supercharging unit, the second scroll structure connecting pipeline (44), and the single-stage mixed flow turbine (13) of the main part, and is then discharged through the tail nozzle (15).

2. The ultra-high pressure ratio compact high efficiency energy-saving turbojet engine according to claim 1, characterized in that: The main body air intake portion (11) comprises a first air intake duct outer cover (111) and a first air intake duct (112); the first air intake duct outer cover (111) and the first air intake duct (112) are connected by means of mutually matching card slots and card blocks; The main body single-stage centrifugal compressor (12) further comprises a first single-stage centrifugal impeller (121), a first diffuser end cover (122), and a first diffuser (123); the radial outer side of the first diffuser end cover (122) is connected to the first air inlet duct outer cover (111) by means of mutually matching slots and blocks; one side of the first diffuser end cover (122) is connected to the first diffuser (123) by means of a flange; the other side of the first diffuser end cover (122) is connected to the first air inlet duct (112) by means of a flange; the side of the first volute-shaped header (124) close to the air inlet direction is connected to the first diffuser end cover (122) by means of mutually matching slots and blocks; the side of the first volute-shaped header (124) close to the air outlet direction is connected to the first diffuser (123) by means of a flange.

3. The ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine according to claim 1, characterized in that: The main body shaft system structure (14) comprises a first shaft body (141), a first shaft sleeve (142), and a first shaft sleeve component (143); the first shaft sleeve (142) and the first shaft sleeve component (143) are connected by interference fit; the first single-stage centrifugal impeller (121) is connected by interference fit to the first shaft body (141) via a center hole; and the first diffuser (123) is connected to the first shaft sleeve (142) via a flange.

4. The ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine according to claim 1, characterized in that: The main body single-stage mixed flow turbine (13) comprises a first volute-shaped air inlet (131), a first turbine guide (132), a first single mixed flow turbine blade (133), a first turbine retaining ring (134), and a first turbine fixing nut (135); the first turbine guide (132) is connected to a first shaft sleeve component (143) by interference fit; the first single mixed flow turbine blade (133) is connected to a first shaft body (141); a center hole of the first single mixed flow turbine blade (133) and the first shaft body (141) are connected to each other; ), the first turbine retaining ring (134) is interference fit with the first shaft (141), and is placed on the front side of the first single mixed flow turbine blade (133) in the intake direction through the first shaft (141); the first turbine fixing nut (135) is interference fit with the first shaft (141), and is placed on the rear side of the first single mixed flow turbine blade (133) in the near direction through the first shaft (141), thereby fixing the first single mixed flow turbine blade (133); the tail nozzle (15) and the first turbine guide (132) are connected by flanges.

5. The ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine according to claim 1, characterized in that: The secondary boost unit air intake portion (21) comprises a second air intake duct outer cover (211) and a second air intake duct (212), wherein the second air intake duct outer cover (211) and the second air intake duct (212) are connected by means of mutually matching card slots and card blocks; The two-stage boost unit single-stage centrifugal compressor (22) comprises a second single-stage centrifugal impeller (221), a second diffuser end cover (222), a second diffuser (223), and a second volute-shaped header (224); the radial outer side of the second diffuser end cover (222) is connected to the second air inlet duct outer cover (211) by means of mutually matching slots and blocks; one side of the second diffuser end cover (222) is connected to the second diffuser (223) by means of a flange; the other side of the second diffuser end cover (222) is connected to the second air inlet duct (212) by means of a flange; the side of the second volute-shaped header (224) close to the air inlet direction is connected to the second diffuser end cover (222) by means of mutually matching slots and blocks; and the side of the second volute-shaped header (224) close to the air outlet direction is connected to the second diffuser (223) by means of a flange.

6. The ultra-high pressure ratio compact high-efficiency energy-saving turbojet engine according to claim 1, characterized in that: The secondary boost unit shaft system structure (24) comprises a second shaft body (241), a second shaft sleeve (242), and a second shaft sleeve component (243); the second shaft sleeve (242) and the second shaft sleeve component (243) are connected by interference fit; the second single-stage centrifugal impeller (221) is connected to the second shaft body (241) by interference fit through a center hole; and the second diffuser (223) is connected to the second shaft sleeve (242) by a flange.

7. The ultra-high pressure ratio compact high efficiency energy-saving turbojet engine according to claim 1, characterized in that: The two-stage supercharging unit single-stage mixed flow turbine (23) comprises a second volute-shaped air inlet (231), a second turbine guide (232), a second single mixed flow turbine blade (233), a second turbine retaining ring (234), and a second turbine fixing nut (235); the second turbine guide (232) is connected to a second shaft sleeve component (243) by interference fit; the second single mixed flow turbine blade (233) is connected to a second shaft body (241); a center hole of the second single mixed flow turbine blade (233) is matched with the second shaft body (241); the second turbine retaining ring (234) is interference fit with the second shaft body (241); and the second shaft body (241) is arranged At the front side of the second single mixed flow turbine blade (233) in the direction of air intake, the second turbine fixing nut (235) is interference fit with the second shaft (241), and is placed at the rear side of the second single mixed flow turbine blade (233) in the direction of air intake through the second shaft (241), thereby fixing the second single mixed flow turbine blade (233). After the airflow flows out through the second single mixed flow turbine blade (233), it flows through the second airflow guide device (236) and flows to the first volute-shaped air intake duct (131) through the scroll structure connecting pipe 2 (42), further driving the first single mixed flow turbine blade (133) of the main body (1) to rotate, generating thrust, and ejecting from the tail nozzle (15).

8. The ultra-high pressure ratio compact high efficiency energy-saving turbojet engine according to claim 1, characterized in that: The air intake portion (31) of the three-stage supercharging combustion unit comprises a third air intake passage (312), the third air intake passage (312) is connected to the scroll structure connecting pipe three (43), and the gas pressurized by the two-stage supercharging unit enters the third air intake passage (312) of the three-stage supercharging combustion unit (3) along the scroll structure connecting pipe three (43), and the three-stage supercharging begins; The three-stage supercharging combustion unit single-stage centrifugal compressor (32) comprises a third single-stage centrifugal impeller (321), a third diffuser (323), and a single-stage centrifugal compressor casing (325); the third air inlet (312) is connected to the single-stage centrifugal compressor casing (325); the third single-stage centrifugal impeller (321) is connected to the third shaft (341) through an interference fit through a center hole; and the third diffuser (323) is connected to the third shaft sleeve (342) through a flange. ; The three-stage supercharged combustion unit shaft system structure (34) comprises a third shaft body (341), a third shaft sleeve (342), and a third shaft sleeve component (343); the third shaft sleeve (342) and the third shaft sleeve component (343) are connected by interference fit.

9. The ultra-high pressure ratio compact high efficiency energy-saving turbojet engine according to claim 1, characterized in that: The single annular combustion chamber (36) comprises a combustion chamber casing (361), an annular combustion chamber (362), and a fuel nozzle (363); the single-stage centrifugal compressor casing (325) is tightly connected to the combustion chamber casing (361); the annular combustion chamber (362) is tightly coupled to the third turbine guide vane (332); and the fuel nozzle (363) is arranged on the annular combustion chamber (362).

10. The ultra-high pressure ratio compact high efficiency energy-saving turbojet engine according to claim 1, characterized in that: The three-stage supercharged combustion unit single-stage mixed flow turbine (33) comprises a third turbine guide (332), a third single mixed flow turbine blade (333), a third turbine retaining ring (334), and a third turbine fixing nut (335); the third turbine guide (332) is connected to the third shaft sleeve component (343) by interference fit; the third single mixed flow turbine blade (333) is connected to the third shaft body (341); the center hole of the third single mixed flow turbine blade (333) is matched with the third shaft body (341); the third turbine retaining ring (334) is interference fit with the third shaft body (341) and is placed on the front side of the third single mixed flow turbine blade (333) in the intake direction through the third shaft body (341); the third turbine fixing nut (335) is interference fit with the third shaft body (341) and is placed on the rear side of the third single mixed flow turbine blade (333) in the near direction through the third shaft body (341), thereby fixing the third single mixed flow turbine blade (333); After the airflow flows out through the third single mixed flow turbine blade (333), it flows through the third airflow guide device (336) to change the gas flow direction, and the gas flows to the second volute-shaped air inlet (231) through the scroll structure connecting pipe four (44), further driving the second single mixed flow turbine blade (233) of the secondary supercharging unit (2) to rotate, thereby generating thrust.

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