A small high performance gas turbine stage power plant

Abstract

The present application relates to a kind of small high-performance gas turbine stage power device, belong to the field of power machinery equipment research and development manufacturing;Shaft axial horizontal arrangement;Turbine disc is installed in the middle position of shaft;Guiding device is installed in the middle position of shaft, and located in the middle position of turbine disc;Rotor moving blade is evenly distributed in the circumferential side wall of turbine disc;Stator stage is installed in one end of shaft, located in the left side of turbine disc;Stator stage is cooperated with shaft by 1 bearing;Turbine intake side seal is installed on the shaft, and located in the left side of turbine disc;Exhaust device is installed in the other end of shaft, located in the right side of turbine disc;Exhaust device is cooperated with shaft by another 1 bearing;Turbine exhaust side seal is installed on the shaft, and located in the right side of turbine disc;The present application has the advantages of high gas turbine stage specific power, small structure size, light weight, high power rotor stability and reliability, good process and economy, etc., can be widely used in the above stage small thrust pump pressure type liquid rocket engine.

Description

Technical Field

[0001] This invention belongs to the field of power machinery equipment research and development and manufacturing, and relates to a small high-performance gas turbine stage power device. Background Technology

[0002] As the heart of a liquid rocket engine, the turbopump is characterized by operating in high temperature, high pressure, high speed, and corrosive media. The turbine stage propulsion unit, as the core component and power source of the propellant supply system for a liquid rocket engine, needs to achieve high efficiency and work capacity. It aims to maximize output power with minimal gas flow, thereby improving the rocket engine's specific impulse, reducing fuel consumption, and enhancing rocket performance and payload capacity. Furthermore, with the development of upper-stage liquid rockets towards higher performance, smaller size, lighter weight, and faster speeds, the turbine propulsion unit requires minimal weight, smaller structural dimensions, and high rotor reliability and stability. Therefore, developing a small, high-performance gas turbine stage propulsion unit is crucial for meeting the demands of future high-performance upper-stage rockets. Currently, this technology remains largely undeveloped. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a small high-performance gas turbine stage power unit with advantages such as high specific power of gas turbine stage, small structural size, light weight, high stability and reliability of power rotor, good manufacturability and economy. It can be widely used in upper stage small thrust pump-fed liquid rocket engines.

[0004] The solution of the present invention is:

[0005] A small, high-performance gas turbine stage power unit includes a stator stage, a turbine disk, a guide device, an exhaust device, a shaft, rotor blades, two bearings, a turbine inlet side seal, and a turbine exhaust side seal.

[0006] The shaft is horizontally oriented; the turbine disk is mounted in the middle of the shaft; the guide device is mounted in the middle of the shaft and located in the center of the turbine disk; the rotor blades are evenly distributed on the circumferential sidewalls of the turbine disk; the stator stage is mounted on one end of the shaft, located on the left side of the turbine disk; the stator stage and the shaft are connected by a bearing; the turbine inlet side seal is mounted on the shaft and located on the left side of the turbine disk; the exhaust device is mounted on the other end of the shaft, located on the right side of the turbine disk; the exhaust device and the shaft are connected by another bearing; the turbine exhaust side seal is mounted on the shaft and located on the right side of the turbine disk; the stator stage and the exhaust device form a cavity; the top outer wall of the stator stage has an inlet, allowing external high-temperature, high-pressure gas to enter the cavity; the external high-temperature, high-pressure gas expands and accelerates through the stator stage, driving the rotor blades to rotate and generate mechanical kinetic energy, producing load power; the bottom outer wall of the exhaust device has an outlet, from which the external high-temperature, high-pressure gas flows out.

[0007] In the aforementioned small high-performance gas turbine stage power unit, the shaft and turbine disk are integrally formed; the turbine disk and rotor blades are integrally formed.

[0008] In the aforementioned small high-performance gas turbine power unit, the turbine disk has a two-stage disk assembly structure, including two disks spaced apart; rotor blades are evenly distributed on the circumferential sidewall of each disk.

[0009] In the aforementioned small high-performance gas turbine power unit, the rotor blades distributed on the upstream turbine disk adopt impingement blades, and the rotor blades distributed on the downstream turbine disk adopt reaction blades; it achieves a power output of 110kW at a gas flow rate of 0.18kg / s, with a power-to-weight ratio of 606kW.s / kg, and a turbine disk main operating efficiency of 39.7%.

[0010] In the aforementioned small high-performance gas turbine stage power unit, each turbine disk has 69 rotor blades distributed circumferentially, which ensures the work capacity of the turbine disk under the flow area and working flow, while avoiding vibration caused by frequency coupling between the turbine disk and the stator stage; each rotor blade is provided with an integrated blade crown at the top; the turbine disk, shaft, rotor blades and blade crown are all integrally formed using high-temperature alloy GH4169 material.

[0011] In the aforementioned small high-performance gas turbine stage power unit, the stator stage has an annular structure; an air inlet is provided at the top of the stator stage; the inner wall of the stator stage is divided into three units along the circumference: a main nozzle unit, a secondary nozzle unit, and a no-inlet unit; the main nozzle unit has six nozzles evenly arranged along the circumference; the secondary nozzle unit has three nozzles evenly arranged along the circumference; the no-inlet unit has no nozzles; all nine nozzles are connected to the air inlet, enabling external high-temperature and high-pressure gas to enter through the air inlet, expand and accelerate through the nozzles, and then enter the cavity formed by the stator stage and the exhaust device; depending on the requirements, the external high-temperature and high-pressure gas can be selected to enter the cavity through the main nozzle unit, through the secondary nozzle unit, or prevented from entering through the no-inlet unit.

[0012] In the aforementioned small, high-performance gas turbine stage power unit, the nozzle of the main nozzle unit adopts a convergent-divergent design profile, with an intake angle of 17°; the equivalent area of ​​a single nozzle throat is 6.60 mm². 2 This enables the turbine disk to continuously generate kinetic energy by introducing high-temperature and high-pressure external gas, ensuring the turbine disk's continuous, reliable, and stable operation.

[0013] In the aforementioned small, high-performance gas turbine stage power unit, the nozzle of the auxiliary nozzle unit adopts a convergent-divergent profile, with an intake angle of 17°; the equivalent area of ​​a single nozzle throat is 10.75 mm². 2 This enables reliable start-up of the turbine disk under external high-temperature and high-pressure gas conditions, ensuring the turbine disk's rapid start-up response capability under conditions not exceeding 0.9s.

[0014] In the aforementioned small high-performance gas turbine stage power unit, the guide device is set at the gap between the two disks to guide the rotation of the turbine disks; the guide device is a disk-mounted structure, and 58 impact blades with blade crowns are evenly distributed on the circumferential sidewall of the guide device.

[0015] In the aforementioned small high-performance gas turbine stage power unit, the exhaust device and the stator stage are electron beam welded, ensuring reliable connection of the cavity gas seal and high-temperature environment; the exhaust device has a thin-walled structure and is not used as a load-bearing component; the main profile of the exhaust device adopts a tapered, smooth transition, convergent irregular structure; the exhaust device is 3D printed in one piece, reducing the spatial size and structural weight of the turbine stage unit.

[0016] The advantages of this invention compared to the prior art are:

[0017] (1) This invention addresses the technical challenges of turbine drive in developing highly reliable, lightweight, miniaturized, and high-performance rocket engines. It has invented a small, high-performance gas turbine stage power unit, breaking through the technology of small, high-performance turbine stage power units with a capacity of hundreds of kilowatts for small-flow open-cycle engines. The turbine unit generates 110 kW of power with a component gas flow rate of only 0.18 kg / s, and its power-to-weight ratio can reach 606 kW·s / kg. The turbine's main operating condition efficiency is tested to reach 39.7%. It also has high reliability, convenient manufacturing, and economical application.

[0018] (2) This invention has the advantages of miniaturization, light weight, high reliability, and good economy: At present, in my country's upper-stage engine turbine power units of hundreds of kilowatts, a single-stage impact blade structure is mostly used, which results in a relatively low power-to-weight ratio and turbine stage efficiency, making the engine less economical. At the same time, in order to ensure the power output, the single-stage rotor disk is large in size, and the overall rigidity and structural reliability are not high, which easily leads to large blade disk vibration and rubbing. The invention is a small high-performance gas turbine stage power unit with a rotor stage center diameter of only 126mm. It is the first to adopt a two-stage combined turbine central placement scheme with local air intake axial, small flow, high pressure differential, and two-stage combined turbine. This not only effectively ensures the high performance of the turbine stage device under small flow, but also improves the working stability and structural reliability of the rotor stage, reduces the weight of the device and reduces its outer dimensions. This invention has now passed the long-distance hot test verification test.

[0019] (3) This invention features fast start-up response, good manufacturability, and high adaptability to various operating conditions: The use of a dedicated start-up nozzle unit and equivalent throat area calculation ensures that high-energy working fluids can be used to generate higher temperatures and pressures to achieve multiple rapid start-up responses for the turbine stage. The use of independent working nozzle units and guide devices ensures sufficient air intake for the small turbine section, reducing potential performance losses due to gas overflow, while also ensuring the stability of the turbine stage under different gas flow rates and operating conditions, thus improving the turbine stage's drive inertia and adaptability to varying operating conditions. The integrated machining of blades, blade crowns, impeller, and shaft simplifies the manufacturing process and flow. The segmented design of the guide device's blade cascade ensures convenient and operable integrated assembly. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the turbine stage power unit of the present invention;

[0021] Figure 2 This is a schematic diagram of the axial direction of the stator stage of the present invention;

[0022] Figure 3 This is a schematic diagram of the rotor blade structure of the present invention;

[0023] Figure 4This is a schematic diagram of the exhaust device structure of the present invention. Detailed Implementation

[0024] The present invention will be further described below with reference to the embodiments.

[0025] To meet the technical requirements of "high performance, small size, light weight, and high speed" for upper-stage liquid rockets, and to address the challenges of turbine drive technology in developing highly reliable, lightweight, miniaturized, and high-performance rocket engines, a small, high-performance gas turbine stage power unit has been invented. This breakthrough has enabled the development of a small, high-performance turbine stage power unit for small-flow open-cycle engines with a capacity of hundreds of thousands of units, while also possessing high reliability, ease of manufacturing, and economical application.

[0026] Small, high-performance gas turbine power units, such as Figure 1 As shown, the turbine assembly specifically includes a stator stage 1, a turbine disk 2, a guide device 3, an exhaust device 4, a shaft 5, rotor blades 6, two bearings 7, a turbine inlet side seal 8, and a turbine exhaust side seal 9. The shaft 5 is axially horizontally positioned. The turbine disk 2 is mounted on the middle of the shaft 5. The guide device 3 is mounted on the middle of the shaft 5, located in the center of the turbine disk 2. The rotor blades 6 are evenly distributed on the circumferential sidewalls of the turbine disk 2. The stator stage 1 is mounted on one end of the shaft 5, located on the left side of the turbine disk 2. The stator stage 1 is connected to the shaft 5 via a bearing 7. The turbine inlet side seal 8 is mounted on the shaft 5 and located on the left side of the turbine disk 2. The exhaust device 4 is mounted on the other end of the shaft 5, located on the right side of the turbine disk 2; the exhaust device 4 and the shaft 5 are connected by another bearing 7; the turbine exhaust side seal 9 is mounted on the shaft 5 and located on the right side of the turbine disk 2; the stator stage 1 and the exhaust device 4 form a cavity; the top outer wall of the stator stage 1 is provided with an air inlet, so that the external high-temperature and high-pressure gas can enter the cavity from the air inlet; the external high-temperature and high-pressure gas expands and accelerates through the stator stage 1, drives the rotor blades 6 to rotate and do work, generate mechanical kinetic energy, and generate load power; the bottom outer wall of the exhaust device 4 is provided with an air outlet, from which the external high-temperature and high-pressure gas flows out.

[0027] After startup, the main nozzle unit of stator stage 1 receives high-temperature, high-pressure combustion gas from the upstream combustion device of the engine according to the engine's preset program. This continuously drives the rotor stage impeller 6, which in turn drives the turbine disk 2 and shaft 5 to rotate. The combustion gas converts thermal energy into mechanical energy within the turbine stage, outputting load power to provide the required power. To improve the efficiency of the small turbine stage and the gas's energy conversion capability, a guide device 3 is designed between the first and second stage impellers. The overall aerodynamic profile of the turbine stage is ensured by the exhaust device 4, and a reliable seal of the turbine stage combustion chamber is achieved by welding one end to the stator stage and the other end to the load-bearing casing. The combustion gas that has completed its work flow through the rotor stage is discharged through the radial exhaust port of the exhaust device 4, ensuring the turbine stage outlet pressure. High-temperature combustion gas sealing devices 8 and 9 are designed on both the inlet and exhaust sides of the turbine rotor stage for axial sealing of the turbine chamber, preventing combustion gas leakage and ensuring the turbine stage's performance, thus guaranteeing the sealing performance and operational reliability of the turbine stage power unit. The turbine stage adopts a two-point symmetrical support. The rotor shaft 5 is supported on the load-bearing casing at the load end by two rolling bearings 7 of the same specification. The load can be installed on both sides of the load-bearing bearing respectively.

[0028] In this invention, the shaft 5 and the turbine disk 2 are integrally formed; the turbine disk 2 and the rotor blade 6 are integrally formed.

[0029] like Figure 3 As shown, turbine disk 2 is a two-stage disk assembly structure, comprising two disks spaced apart; rotor blades 6 are evenly distributed on the circumferential sidewalls of each disk. The rotor blades 6 distributed on the upstream disk are impingement blades, while the rotor blades 6 distributed on the downstream disk are reaction blades; achieving a power output of 110kW at a gas flow rate of 0.18kg / s, with a power-to-weight ratio of 606kW·s / kg, and a main operating efficiency of 39.7% for turbine disk 2.

[0030] Each rotor disk has 69 rotor blades 6 distributed circumferentially, which ensures the work capacity of the turbine disk 2 under the flow area and working flow, while avoiding vibration caused by frequency coupling between the turbine disk 2 and the stator stage 1; each rotor blade 6 is provided with an integrated blade crown at the top; the turbine disk 2, shaft 5, rotor blades 6 and blade crown are all integrally formed using high-temperature alloy GH4169 material.

[0031] like Figure 2As shown, the stator stage 1 has an annular structure; an air inlet is provided at the top of the stator stage 1; the inner wall of the stator stage 1 is divided into three units along the circumference: a main nozzle unit, a secondary nozzle unit, and a no-inlet unit; the main nozzle unit has six nozzles evenly arranged along the circumference; the secondary nozzle unit has three nozzles evenly arranged along the circumference; the no-inlet unit has no nozzles; all nine nozzles are connected to the air inlet, allowing external high-temperature and high-pressure gas to enter through the air inlet, expand and accelerate through the nozzles, and then enter the cavity formed by the stator stage 1 and the exhaust device 4; depending on the requirements, the external high-temperature and high-pressure gas can be selected to enter the cavity through the main nozzle unit, through the secondary nozzle unit, or prevented from entering through the no-inlet unit.

[0032] Preferably, the main nozzle unit's nozzles adopt a convergent-divergent design profile with an intake angle of 17°; the equivalent area of ​​a single nozzle throat is 6.60 mm². 2 This enables the turbine disk 2 to continuously generate kinetic energy by introducing external high-temperature and high-pressure gas into it, thus ensuring the turbine disk 2 can operate continuously, reliably, and stably.

[0033] The nozzle of the secondary nozzle unit adopts a convergent-divergent profile, with an intake angle of 17°; the equivalent area of ​​a single nozzle throat is 10.75 mm². 2 This enables the turbine disk 2 to start reliably under external high temperature and high pressure gas conditions, and ensures the turbine disk 2's rapid start-up response capability under conditions of no more than 0.9s.

[0034] The guide device 3 is set at the gap between the two disks to guide the rotation of the turbine disk 2; the guide device 3 is a disk-mounted structure, and 58 impact blades with blade crowns are evenly distributed on the circumferential sidewall of the guide device 3.

[0035] like Figure 4 As shown, the exhaust device 4 and the stator stage 1 are electron beam welded, ensuring the reliability of the cavity gas sealing and connection under high temperature conditions; the exhaust device 4 is a thin-walled structure and is not used as a load-bearing component; the main surface of the exhaust device 4 adopts a tapered, smooth transition, convergent irregular structure; the exhaust device 4 is 3D printed in one piece, reducing the spatial size and structural weight of the turbine stage.

[0036] The guide stage device 3 of this invention adopts an axial flow blade cascade structure located between the two-stage rotor blades for intake of air into the second-stage turbine impeller. To improve the efficiency of the small turbine stage device, the guide stage 1 is designed with 58 impact blades with blade crowns, integrally machined and arranged circumferentially as a partial blade cascade structure, consisting of three arcs, corresponding to the main nozzle unit and auxiliary nozzle unit positions of the stator stage, respectively. Its circumferential arc accounts for 68.6%, and it is fixedly installed on the turbine stator stage 1 with 9 bolts, further improving the manufacturability and maintainability of the turbine stage device.

[0037] One end of the exhaust device 4 is connected to the turbine stator stage via an mounting ring using electron beam welding to ensure the reliability of the turbine cavity gas seal and connection under high-temperature conditions. The other end is fixed to the support shell via welding with a flange. It is mainly used to ensure the aerodynamic shape of the turbine stage gas flow channel and to discharge the gas after the drive turbine has done work to the outside. The exhaust device is not a load-bearing component in the turbine stage power unit and is designed as a thin-walled structure. Its main profile adopts a tapered, smooth transition, convergent irregular shape structure, with local exhaust holes. The position corresponds to the stator stage inlet nozzle. It is 3D printed as a single piece, which effectively reduces the spatial size and structural weight of the turbine stage unit.

[0038] The invention of a small, high-performance gas turbine stage power unit was used to complete a long-term test of a certain type of advanced upper stage power unit, breaking through the key technical challenges of small, lightweight, high-performance, fast-response, and long-life turbine stage power units.

[0039] This invention addresses the challenges of turbine drive technology in developing highly reliable, lightweight, miniaturized, and high-performance rocket engines. It proposes a small, high-performance gas turbine stage power unit, breaking through the technology of small, high-performance turbine stage power units for low-flow open-cycle engines with a capacity of hundreds of kilowatts. The turbine unit generates 110 kW of power with a component gas flow rate of only 0.18 kg / s, achieving a power-to-weight ratio of 606 kW·s / kg. The tested turbine main operating condition efficiency reaches 39.7%, while also possessing high reliability, ease of manufacture, and economical application.

[0040] This invention offers advantages such as miniaturization, light weight, high reliability, and good economy. Currently, most turbine power units in my country's upper-stage engines with a capacity of 100 kilowatts adopt a single-stage impact blade structure, resulting in relatively low power-to-weight ratio and turbine stage efficiency, leading to poor engine economy. Furthermore, to ensure work capacity, the single-stage rotor disk is relatively large, resulting in low overall rigidity and structural reliability, and is prone to significant disk vibration and rubbing. This invention presents a small, high-performance gas turbine power unit with a rotor stage mid-diameter of only 126 mm. It is the first to adopt a two-stage combined turbine mid-mounted scheme with partial axial intake, low flow rate, high pressure differential, and effectively ensures high performance of the turbine stage at low flow rates. It also improves rotor stage operating stability and structural reliability, reduces device weight, and minimizes its overall dimensions. This technological invention has already passed long-duration hot-fire testing verification.

[0041] This invention features rapid start-up response, excellent manufacturability, and high adaptability to various operating conditions: It employs a specialized start-up nozzle unit and equivalent throat area calculations to ensure that high-energy working fluids can be used to generate higher temperatures and pressures, enabling multiple rapid start-up responses for the turbine stage. The use of independent working nozzle units and guide devices ensures adequate air intake for the small turbine section, reducing potential performance losses due to gas overflow, while also guaranteeing the stability of the turbine stage under different gas flow rates and operating conditions, thus improving the turbine stage's drive inertia and adaptability to varying operating conditions. The integrated machining of blades, blade crowns, impeller, and shaft simplifies the manufacturing process, and the segmented design of the guide device's blade cascade ensures convenient and easy-to-operate integrated assembly.

[0042] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A small, high-performance gas turbine stage power unit, characterized in that: It includes a stator stage (1), a turbine disk (2), a guide device (3), an exhaust device (4), a shaft (5), rotor blades (6), two bearings (7), a turbine inlet side seal (8), and a turbine exhaust side seal (9); The shaft (5) is horizontally axially positioned; the turbine disk (2) is mounted on the middle of the shaft (5); the guide device (3) is mounted on the middle of the shaft (5) and located in the center of the turbine disk (2); the rotor blades (6) are evenly distributed on the circumferential sidewalls of the turbine disk (2); the stator stage (1) is mounted on one end of the shaft (5) and located on the left side of the turbine disk (2); the stator stage (1) and the shaft (5) are connected by a bearing (7); the turbine intake side seal (8) is mounted on the shaft (5) and located on the left side of the turbine disk (2); and the exhaust device (4) is mounted on the other end of the shaft (5) and located on the turbine disk (2). The right side; the exhaust device (4) and the shaft (5) are connected by another bearing (7); the turbine exhaust side seal (9) is fitted on the shaft (5) and located on the right side of the turbine disk (2); the stator stage (1) and the exhaust device (4) form a cavity; the top outer wall of the stator stage (1) is provided with an air inlet, so that the external high temperature and high pressure gas enters the cavity from the air inlet; the external high temperature and high pressure gas expands and accelerates through the stator stage (1), drives the rotor blades (6) to rotate and do work, generate mechanical kinetic energy, and generate load power; the bottom outer wall of the exhaust device (4) is provided with an air outlet, so that the external high temperature and high pressure gas flows out from the air outlet.

2. The small high-performance gas turbine stage power unit according to claim 1, characterized in that: The shaft (5) and the turbine disk (2) are integrally formed; the turbine disk (2) and the rotor blades (6) are integrally formed.

3. The small high-performance gas turbine stage power unit according to claim 1, characterized in that: The turbine disk (2) is a two-stage disk assembly structure, including two disks with a gap between them; rotor blades (6) are evenly distributed on the circumferential sidewall of each disk.

4. A small high-performance gas turbine stage power unit according to claim 3, characterized in that: The rotor blades (6) distributed on the upstream wheel disk adopt impact blades, and the rotor blades (6) distributed on the downstream wheel disk adopt reaction blades; to achieve a power of 110kW at a gas flow rate of 0.18kg / s, the power-to-weight ratio reaches 606kW.s / kg, and the main working efficiency of the turbine disk (2) reaches 39.7%.

5. A small high-performance gas turbine stage power unit according to claim 4, characterized in that: Each rotor disk has 69 rotor blades (6) distributed circumferentially, which ensures the working capacity of the turbine disk (2) under the flow area and working flow, while avoiding vibration caused by frequency coupling between the turbine disk (2) and the stator stage (1); each rotor blade (6) is provided with an integrated blade crown at the top; the turbine disk (2), shaft (5), rotor blades (6) and blade crown are all integrally formed using high-temperature alloy GH4169 material.

6. A small high-performance gas turbine stage power unit according to claim 1, characterized in that: The stator stage (1) has an annular structure; an air inlet is provided at the top of the stator stage (1); the inner wall of the stator stage (1) is divided into three units along the circumference, namely the main nozzle unit, the auxiliary nozzle unit and the no-inlet unit; the main nozzle unit has six nozzles evenly arranged along the circumference; the auxiliary nozzle unit has three nozzles evenly arranged along the circumference; the no-inlet unit has no nozzles; all nine nozzles are connected to the air inlet, so that the external high-temperature and high-pressure gas enters through the air inlet, and after being expanded and accelerated by the nozzles, it enters the cavity formed by the stator stage (1) and the exhaust device (4); according to the requirements, the external high-temperature and high-pressure gas can be selected to enter the cavity through the main nozzle unit, enter the cavity through the auxiliary nozzle unit, or prevent the external high-temperature and high-pressure gas from entering through the no-inlet unit.

7. A small high-performance gas turbine stage power unit according to claim 6, characterized in that: The main nozzle unit employs a convergent-divergent nozzle design with an intake angle of 17°; the equivalent area of ​​a single nozzle throat is 6.60 mm². 2 This enables the turbine disk (2) to continuously generate kinetic energy by introducing external high-temperature and high-pressure gas into the turbine disk (2), ensuring the turbine disk (2) to work continuously, reliably and stably.

8. A small high-performance gas turbine stage power unit according to claim 7, characterized in that: The nozzle of the secondary nozzle unit adopts a convergent-divergent profile, with an intake angle of 17°; the equivalent area of ​​a single nozzle throat is 10.75 mm². 2 This enables the turbine disk (2) to start reliably under external high temperature and high pressure gas conditions, and ensures the turbine disk (2) has a rapid start-up response capability under conditions of no more than 0.9s.

9. A small high-performance gas turbine stage power unit according to claim 3, characterized in that: The guide device (3) is set at the gap between the two disks to guide the rotation of the turbine disk (2); the guide device (3) is a disk-mounted structure, and 58 impact blades with blade crowns are evenly distributed on the circumferential sidewall of the guide device (3).

10. A small high-performance gas turbine stage power unit according to claim 3, characterized in that: The exhaust device (4) and the stator stage (1) are connected by electron beam welding, which ensures the reliability of the gas sealing in the cavity and the connection under high temperature conditions. The exhaust device (4) is a thin-walled structure and is not used as a load-bearing component. The main surface of the exhaust device (4) adopts a tapered, smooth transition, convergent irregular structure. The exhaust device (4) is 3D printed in one piece, which reduces the spatial size and structural weight of the turbine stage.

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