WO2024045240A1

WO2024045240A1 - Supercritical carbon dioxide radial-inflow turbine structure suitable for gas inlet at 600 ℃

Info

Publication number: WO2024045240A1
Application number: PCT/CN2022/120425
Authority: WO
Inventors: 徐殿吉; 魏红阳; 徐鹏; 张春秀; 邢冠一; 郭庆丰; 翟彦恺; 王成佳; 刘阳; 杨一鸣; 吕天昊
Original assignee: 哈电发电设备国家工程研究中心有限公司; 哈尔滨汽轮机厂有限责任公司
Priority date: 2022-09-01
Filing date: 2022-09-22
Publication date: 2024-03-07
Also published as: CN115324669A

Abstract

A supercritical carbon dioxide radial-inflow turbine structure suitable for gas inlet at 600 ℃, belonging to the technical field of turbines. The present invention aims to solve the problem that sealing of supercritical carbon dioxide turbines is difficult at 25 MPa-600 ℃. The structure comprises a low-pressure radial-inflow turbine, a gearbox and a high-pressure radial-inflow turbine; a rotor with cantilevers at both ends is provided on the gearbox, one end of the rotor passing through a low-pressure sealed casing and a low-pressure heat-insulation casing of the low-pressure radial-inflow turbine to extend into a low-pressure volute, and being connected to a low-pressure centripetal impeller; the low-pressure sealed casing is connected to the rotor by means of a dry gas seal, and a low-temperature carbon dioxide gas source is communicated with the interior of the low-pressure sealed casing by means of a pipeline; the other end of the rotor and the high-pressure radial-inflow turbine have a cooperation relationship the same as that with the low-pressure end. A low-temperature carbon dioxide gas is introduced from the outside to cool the dry gas seals, thus solving the problem that sealing of supercritical carbon dioxide turbines is difficult at high gas inlet parameters of 25 MPa-600 ℃.

Description

A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake

Technical field

The invention belongs to the field of turbine technology, and in particular relates to a supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake.

Background technique

The traditional power generation system uses the steam Rankine cycle, and the efficiency of the 600°C ultra-supercritical coal-fired primary reheat unit is 44.5%. However, the 700°C ultra-supercritical steam cycle that achieves higher efficiency faces difficulties in developing nickel-based superalloy materials, high-temperature boilers and Problems such as difficulty in steam turbine layout and high investment costs make it difficult to implement at present.

The supercritical carbon dioxide cycle power generation system has the advantages of clean and efficient, compact structure, and flexible start and stop. It can reach the efficiency of the steam Rankine cycle of 700°C at a temperature of 600°C. It has good technological inheritance and can be realized based on existing materials.

The turbine is the core component of the supercritical carbon dioxide cycle generator set and has a decisive influence on the cycle efficiency. High-temperature and high-pressure carbon dioxide enters the turbine, driving the turbine to do work and driving the generator to generate electricity. In order to pursue the equivalent of 700℃ ultra-supercritical steam power generation To achieve high efficiency, the temperature and pressure of the system's thermodynamic cycle must be increased, requiring the supercritical carbon dioxide thermodynamic cycle pressure to reach 25MPa and the temperature to reach 600°C. Due to the high internal pressure and temperature of the turbine, traditional seals such as comb teeth and carbon rings can no longer meet the requirements. Sealing requirements.

technical problem

The purpose of the present invention is to provide a supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake, so as to solve the problem of difficult sealing of supercritical carbon dioxide turbines at 25MPa-600°C.

Technical solutions

A supercritical carbon dioxide radial turbine structure adapted to 600°C air intake, including a low-pressure radial turbine, a gearbox and a high-pressure radial turbine;

The gearbox includes a rotor, a bearing and a gearbox shell. The rotor rotates on the gearbox shell through the bearing. The two ends of the gearbox shell are respectively equipped with oil retaining rings that match the rotor;

The low-pressure radial turbine includes a low-pressure volute, a low-pressure radial impeller, a low-pressure heat-insulated casing, and a low-pressure sealed casing; the low-pressure volute, the low-pressure heat-insulated casing, and the low-pressure sealed casing are coaxially flanged in sequence, and the low-pressure sealing machine The other end of the casing is connected to the gearbox shell. One end of the rotor passes through the low-pressure sealed casing and the low-pressure insulated casing in sequence, and extends into the low-pressure volute, and matches the low-pressure centripetal impeller stop. The low-pressure centripetal impeller One end of the low-pressure impeller sleeve is equipped with a low-pressure impeller sleeve. The outer circumference of the rotor and the inner circumference of the low-pressure impeller sleeve are matched through a spline structure. A dry gas seal is provided in the low-pressure sealed casing. The low-pressure sealed casing is connected to the rotor through a dry gas seal. , the low-temperature carbon dioxide gas source is connected to the interior of the low-pressure sealed casing through pipelines. The inner hole of the low-pressure heat-insulating casing is provided with low-pressure end sealing teeth. The low-pressure end sealing teeth fit with the outer periphery of the low-pressure impeller sleeve. The low-pressure A number of low-pressure guide vanes are arranged on the upper circumference of the heat-insulating casing, and a number of low-pressure guide vanes are located on the air inlet channel on the outer periphery of the low-pressure centripetal impeller;

The high-pressure radial turbine includes a high-pressure volute, a high-pressure radial impeller, a high-pressure heat-insulated casing, and a high-pressure sealed casing; the high-pressure volute, the high-pressure heat-insulated casing, and the high-pressure sealed casing are coaxially flanged in sequence, and the high-pressure sealing machine The other end of the casing is connected to the gearbox shell. The other end of the rotor passes through the high-pressure sealed casing and the high-pressure heat-insulated casing in sequence, and extends into the high-pressure volute, and matches the high-pressure centripetal impeller seam. One end of the impeller is equipped with a high-pressure impeller sleeve. The outer circumference of the rotor and the inner circumference of the high-pressure impeller sleeve are matched through a spline structure. A dry gas seal is provided in the high-pressure sealed casing. The high-pressure sealed casing is connected to the rotor through a dry gas seal. Connected, the low-temperature carbon dioxide gas source is connected to the interior of the high-pressure sealed casing through pipelines. The inner hole of the high-pressure insulated casing is provided with high-pressure end sealing teeth, and the high-pressure end sealing teeth cooperate with the outer periphery of the high-pressure impeller sleeve. A number of high-pressure guide vanes are arranged on the upper circumference of the high-pressure insulated casing, and a number of high-pressure guide vanes are located on the air inlet channel around the periphery of the high-pressure centripetal impeller.

Further, several low-pressure guide vanes are integrally formed with the low-pressure heat-insulating casing respectively. The tops of the several low-pressure guide vanes are connected through the first annular shroud. The low-pressure volute is provided with a first annular groove, and the first annular shroud is connected to the low-pressure volute. The first annular groove matches, a plurality of high-pressure guide vanes are integrally formed with the high-pressure heat-insulating casing, the tops of several high-pressure guide vanes are connected through a second annular shroud, and a second annular groove is provided on the high-pressure volute. A second annular shroud matches the second annular groove.

Further, a first abradable coating is provided on the inner cavity wall of the low-pressure volute, and the first abradable coating is located in the matching gap area between the low-pressure volute and the low-pressure radial impeller, and is provided on the inner cavity wall of the high-pressure volute. A second abradable coating is provided, and the second abradable coating is located in the matching gap area between the high-pressure volute and the high-pressure radial impeller.

Further, a low-pressure bracket is provided below the low-pressure volute, and a high-pressure bracket is provided below the high-pressure volute.

Further, a heat insulation pad is provided between the low-pressure volute and the low-pressure bracket, and a heat insulation pad is provided between the high-pressure volute and the high-pressure bracket.

Further, the circumferential direction of the low-pressure volute is matched with the low-pressure bracket through the first guide key, and the circumferential direction of the high-pressure volute is matched with the high-pressure bracket through the second guide key.

Furthermore, the high-pressure volute and the high-pressure heat-insulating casing are sealed by a C-type sealing ring, and the low-pressure volute and the low-pressure heat-insulating casing are sealed by a C-type sealing ring.

Further, the bearing is a tilting pad bearing.

Further, the rotation speed of the rotor is 32000r/min.

Furthermore, the high-pressure sealed casing is made of GH4169 material, the high-pressure insulated casing is made of GH4169 material, the high-pressure radial impeller is made of GH4169 material, the high-pressure volute is made of GH4169 volute, and the low-pressure sealed casing is made of GH4169 material. cassette, the low-pressure heat-insulated casing is made of GH4169 material, the low-pressure radial impeller is made of GH4169 material, and the low-pressure volute is made of GH4169 material volute.

beneficial effects

Compared with the prior art, the beneficial effects of the present invention are:

1. The present invention adopts a structural layout scheme in which high and low pressure two-stage radial turbines are connected in series and arranged back-to-back symmetrically on both sides of the reduction gearbox. The turbine has good sealing performance, the seal can work normally at a high temperature of 600°C, and the impeller and The gap between the volutes is small, the guide vanes are stable, and the volutes at both ends and the rotor can be aligned in the center when heated. It is a high-parameter (25MPa/600℃) small-capacity (MW-level) super Critical CO2 turbine design provides a structural solution.

2. The high and low pressure end vents are sealed by dry gas sealing. Low-temperature CO2 gas is introduced from the outside to cool the dry gas seal, which solves the problem of difficulty in sealing supercritical carbon dioxide turbines with high air intake parameters of 25MPa-600℃. .

3. The mating areas of the volute and the centripetal impeller at the high and low pressure ends are equipped with abradable sealing coatings. The excess coating is worn away when the centripetal impeller rotates, achieving a small gap design between the centripetal impeller and the volute to ensure turbine smoothness. While being highly efficient, it also takes into account the safety of turbine operation.

4. The guide vanes at the high and low pressure ends are integrally processed with the heat-insulating casing on the same side. The top of the guide vanes is welded with an annular shroud. At the same time, an annular groove structure is set on the corresponding volute to cooperate with the annular shroud installation. This ensures that the guide vanes work stably and efficiently under the conditions of heat and pressure deformation of the volutes at the high and low pressure ends.

5. Insulation pads are installed between the volutes and the brackets at the high and low pressure ends, and the guide keys can ensure that the volutes and rotors at both ends are centered when heated.

Description of drawings

Figure 1 is a schematic structural diagram of the present invention;

Figure 2 is a schematic structural diagram of a low-pressure radial turbine;

Figure 3 is a schematic diagram of the cooperation between the low-pressure volute and the low-pressure bracket;

Figure 4 is an exploded schematic view of the low-voltage heat-insulating casing and the first annular shroud;

Figure 5 is an enlarged view of point A in Figure 2;

Figure 6 is an enlarged view of B in Figure 2;

Figure 7 is a schematic structural diagram of the gearbox;

Figure 8 is a schematic structural diagram of a high-pressure radial turbine;

Figure 9 is a schematic diagram of the cooperation between the high-pressure volute and the high-pressure bracket;

Figure 10 is an exploded schematic view of the high-pressure insulated casing and the second annular shroud;

Figure 11 is an enlarged view of C in Figure 8;

Figure 12 is an enlarged view of D in Figure 8;

In the picture: 1-low-pressure radial turbine, 11-low-pressure volute, 111-first abradable coating, 12-low-pressure radial impeller, 13-low-pressure heat-insulating casing, 131-low-pressure guide vane, 132- The first annular shroud, 133-low-pressure end sealing teeth, 14-dry gas seal, 15-low-pressure sealing casing, 16-first guide key, 17-low-pressure bracket, 18-low-pressure fastening bolt, 19-heat insulation pad , 2-gearbox, 21-gearbox shell, 22-oil retaining ring, 23-rotor, 24-bearing, 3-high-pressure radial turbine, 31-high-pressure volute, 311-second wearable coating, 32-High-pressure radial impeller, 33-High-pressure heat-insulating casing, 331-High-pressure guide vane, 332-Second annular shroud, 333-High-pressure end sealing teeth, 34-High-pressure fastening bolts, 35-High-pressure sealing casing , 36-second guide key, 37-high pressure bracket.

Embodiments of the invention

In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention is described below through the specific embodiments shown in the drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the invention. Furthermore, in the following description, descriptions of well-known structures and techniques are omitted to avoid unnecessarily confusing the concepts of the present invention.

The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection, including but not limited to conventional fixed connection methods such as flange connection, rivet connection, adhesive connection and welding connection. Detachable connections include but are not limited to conventional disassembly methods such as bolt connections, snap connections, pin connections, and hinge connections. When the specific connection method is not clearly defined, by default, at least one connection method can be found among the existing connection methods to achieve this function. Those skilled in the art can make their own choices as needed. For example: choose welding connection for fixed connection, and choose bolt connection for detachable connection.

The present invention will be further described in detail below with reference to the accompanying drawings. The following examples are explanations of the present invention, but the present invention is not limited to the following examples.

Example: As shown in Figure 1-12, a supercritical carbon dioxide radial turbine structure adapted to 600°C air intake includes a low-pressure radial turbine 1, a gearbox 2 and a high-pressure radial turbine 3;

The gearbox 2 includes a rotor 23, a bearing 24 and a gearbox shell 31. The rotor 23 is rotated on the gearbox shell 31 through the bearing 24. The two ends of the gearbox shell 31 are respectively provided with oil retaining rings that match the rotor 23. twenty two;

The low-pressure radial turbine 1 includes a low-pressure volute 11, a low-pressure radial impeller 12, a low-pressure heat-insulating casing 13, and a low-pressure sealed casing 15; the low-pressure volute 11, the low-pressure heat-insulating casing 13, and the low-pressure sealed casing 15 are the same in sequence. The shaft flange connection, the other end of the low-pressure sealed casing 15 is connected to the gearbox housing 31, one end of the rotor 23 passes through the low-pressure sealed casing 15 and the low-pressure heat-insulating casing 13 in sequence, and extends into the low-pressure volute 11. And it cooperates with the low-pressure radial impeller 12. One end of the low-pressure radial impeller 12 is provided with a low-pressure impeller sleeve. The outer circumference of the rotor 23 and the inner circumference of the low-pressure impeller sleeve are matched through a spline structure, and the low-pressure sealing casing 15 There is a dry gas seal 14 inside. The low-pressure sealed casing 15 is connected to the rotor 23 through the dry gas seal 14. The low-temperature carbon dioxide gas source is connected to the inside of the low-pressure sealed casing 15 through pipelines. The inner hole of the low-pressure heat-insulating casing 13 is provided with The low-pressure end sealing teeth 133 are clearance matched with the outer periphery of the low-pressure impeller sleeve. A plurality of low-pressure guide vanes 131 are provided on the upper circumference of the low-pressure insulated casing 13. A plurality of low-pressure guide vanes 131 are located at the low pressure On the air inlet passage around the periphery of the radial impeller 12;

The high-pressure radial turbine 3 includes a high-pressure volute 31, a high-pressure radial impeller 32, a high-pressure heat-insulated casing and a high-pressure sealed casing 35; the high-pressure volute 31, the high-pressure heat insulated casing and the high-pressure sealed casing 35 are coaxial in sequence. The other end of the high-pressure sealed casing 35 is connected to the gearbox housing 31. The other end of the rotor 23 passes through the high-pressure sealed casing 35 and the high-pressure heat-insulated casing in sequence, and extends into the high-pressure volute 31, and is connected with the gear box casing 31. The high-pressure radial impeller 32 is fitted with a stop. One end of the high-pressure radial impeller 32 is provided with a high-pressure impeller sleeve. The outer circumference of the rotor 23 and the inner circumference of the high-pressure impeller sleeve are matched through a spline structure. The high-pressure sealing casing 35 is provided with There is a dry gas seal 14. The high-pressure sealed casing 35 is connected to the rotor 23 through the dry gas seal 14. The low-temperature carbon dioxide gas source is connected to the inside of the high-pressure sealed casing 35 through a pipeline. The inner hole of the high-pressure insulated casing is provided with a high-pressure end seal. Teeth 333, the high-pressure end sealing teeth 333 are clearance matched with the outer periphery of the high-pressure impeller sleeve. A number of high-pressure guide vanes 331 are provided on the upper circumference of the high-pressure heat insulated casing. A number of high-pressure guide vanes 331 are located on the high-pressure centripetal impeller 32. On the outer air intake channel.

The high and low pressure end vents are sealed by dry gas sealing. Low-temperature CO2 gas is introduced from the outside to cool the dry gas seal, which solves the problem of difficulty in sealing supercritical carbon dioxide turbines with high air intake parameters of 25MPa-600℃.

A plurality of low-pressure guide vanes 131 are respectively integrally formed with the low-pressure heat-insulating casing 13. The tops of the plurality of low-pressure guide vanes 131 are connected through a first annular shroud 132. The low-pressure volute 11 is provided with a first annular groove, and the first annular shroud is provided with a first annular groove. The belt 132 matches the first annular groove, a plurality of high-pressure guide vanes 331 are integrally formed with the high-pressure heat-insulating casing, and the tops of a plurality of high-pressure guide vanes 331 are connected through a second annular shroud 332, and the high-pressure volute 31 is A second annular groove is provided, and the second annular shroud 332 matches the second annular groove.

The guide vanes at the high and low pressure ends are integrally processed with the heat-insulating casing on the same side. The top of the guide vanes is welded with an annular shroud. At the same time, an annular groove structure is set on the corresponding volute to cooperate with the annular shroud installation to ensure high , the guide vanes work stably and efficiently under the conditions of heat and pressure deformation of the volute at the low-pressure end.

The first abradable coating 111 is provided on the inner cavity wall of the low-pressure volute 11. The first abradable coating 111 is provided in the matching gap area between the low-pressure volute 11 and the low-pressure radial impeller 12. The inner wall of the high-pressure volute 31 A second abradable coating 311 is provided on the cavity wall, and the second abradable coating 311 is provided in the matching gap area between the high-pressure volute 31 and the high-pressure radial impeller 32 .

The mating areas of the volute and the centripetal impeller at the high and low pressure ends are equipped with abradable sealing coatings. The excess coating is worn away when the centripetal impeller rotates, achieving a small gap design between the centripetal impeller and the volute to ensure high turbine efficiency. At the same time, the safety of turbine operation is taken into consideration.

A low-pressure bracket 17 is provided below the low-pressure volute 11 , and a high-pressure bracket 37 is provided below the high-pressure volute 31 .

A heat insulation pad 19 is provided between the low-pressure volute 11 and the low-pressure bracket 17 , and a heat insulation pad 19 is provided between the high-pressure volute 31 and the high-pressure bracket 37 .

The circumferential direction of the low-pressure volute 11 is matched with the low-pressure bracket 17 through the first guide key 16 , and the circumferential direction of the high-pressure volute 31 is matched with the high-pressure bracket 37 through the second guide key 36 .

Heat insulation pads are installed between the volutes and the brackets at the high and low pressure ends, and the guide keys can ensure that the volutes and rotors at both ends are centered when heated.

The high-pressure volute 31 and the high-pressure heat-insulating casing are sealed by a C-shaped sealing ring, and the low-pressure volute 11 and the low-pressure heat-insulating casing 13 are sealed by a C-shaped sealing ring.

The bearing 24 is a tilting pad bearing 24.

The rotation speed of rotor 23 is 32000r/min.

The high-pressure sealed casing 35 is made of GH4169 material, the high-pressure insulated casing 32 is made of GH4169 material, the high-pressure radial impeller 32 is made of GH4169 material, the high-pressure volute 31 is made of GH4169 material, and the low-pressure sealed casing 15 is made of GH4169 material. The low-pressure insulated casing 13 is made of GH4169 material, the low-pressure radial impeller 12 is made of GH4169 material, and the low-pressure volute 11 is made of GH4169 material. Choose high-temperature-resistant alloy materials to meet the use requirements of high temperatures of 600°C.

The low-pressure radial turbine 1 and the high-pressure radial turbine 3 use gas with a certain pressure to perform adiabatic expansion in the turbine to perform external work and consume the internal energy of the gas. The turbine in this application is a centripetal turbine, and the gas is vertical to It flows into the turbine along the radial direction in the plane of the rotating shaft, passes through the guide vanes and the rotating impeller in sequence, and then flows out in the axial direction.

In this application, the carbon dioxide gas flow flows into the turbine from the high-pressure volute inlet. After flowing through the high-pressure guide vane and the high-pressure impeller, it flows out from the high-pressure turbine outlet. The carbon dioxide gas flowing out of the high-pressure volute passes through the intermediate pipe and enters the low-pressure volute inlet. , The structure of the low-pressure turbine is similar to that of the high-pressure turbine. After the airflow enters the low-pressure volute inlet (not shown in the figure), it flows through the low-pressure guide vane and the low-pressure impeller in sequence, and then flows out from the low-pressure turbine outlet.

The rotor 23 is provided with a high-speed gear. The high-speed gear meshes with the driving wheel. The driving wheel is sleeved on the output shaft of the driving motor. The driving motor operates to drive the low-pressure radial impeller 12 and the high-pressure radial impeller 32 through gear transmission. Rotate in corresponding volutes respectively. This part is not shown in the drawings, but this part and other undescribed parts are existing technologies and can be selected from published documents.

The above embodiments are only illustrative illustrations of this patent and do not limit its scope of protection. Persons skilled in the art can also make partial changes to them. As long as the spirit and essence of this patent are not exceeded, they are all within the scope of protection of this patent.

Claims

A supercritical carbon dioxide radial turbine structure adapted to 600°C air intake, which is characterized by: including a low-pressure radial turbine (1), a gearbox 2 and a high-pressure radial turbine (3);

The gearbox 2 includes a rotor (23), a bearing (24) and a gearbox housing (31). The rotor (23) is rotated on the gearbox housing (31) through the bearing (24). The gearbox housing (31) Both ends are respectively equipped with oil retaining rings (22) that match the rotor (23);

The low-pressure radial turbine (1) includes a low-pressure volute (11), a low-pressure radial impeller (12), a low-pressure heat-insulated casing (13), and a low-pressure sealed casing (15); the low-pressure volute (11), the low-pressure isolator The thermal casing (13) and the low-pressure sealed casing (15) are connected with coaxial flanges in sequence. The other end of the low-pressure sealed casing (15) is connected to the gearbox housing (31), and one end of the rotor (23) passes through it in sequence. The low-pressure sealed casing (15) and the low-pressure heat-insulating casing (13) extend into the low-pressure volute (11) and match the stop of the low-pressure radial impeller (12). One end of the low-pressure radial impeller (12) A low-pressure impeller sleeve is provided. The outer circumference of the rotor (23) and the inner circumference of the low-pressure impeller sleeve are matched through a spline structure. A dry gas seal (14) is provided in the low-pressure sealing casing (15). The low-pressure sealing casing (15) is connected to the rotor (23) through the dry gas seal (14). The low-temperature carbon dioxide gas source is connected to the interior of the low-pressure sealed casing (15) through the pipeline. The inner hole of the low-pressure insulated casing (13) is provided with a low-pressure end. Sealing teeth (133). The low-pressure end sealing teeth (133) fit with the outer circumference of the low-pressure impeller sleeve. A number of low-pressure guide vanes (131) are provided on the upper circumference of the low-pressure insulated casing (13). The guide vanes (131) are located on the air inlet passage on the outer periphery of the low-pressure radial impeller (12);

The high-pressure radial turbine (3) includes a high-pressure volute (31), a high-pressure radial impeller (32), a high-pressure heat-insulated casing and a high-pressure sealed casing (35); a high-pressure volute (31), a high-pressure heat-insulated casing The high-pressure sealing casing (35) is coaxially flange connected in sequence. The other end of the high-pressure sealing casing (35) is connected to the gearbox housing (31). The other end of the rotor (23) passes through the high-pressure sealing casing (35) in sequence. 35) and the high-pressure heat-insulating casing, and extends into the high-pressure volute (31), and cooperates with the high-pressure radial impeller (32). One end of the high-pressure radial impeller (32) is equipped with a high-pressure impeller pipe sleeve, and the rotor The outer circumference of (23) and the inner circumference of the high-pressure impeller sleeve are matched through a spline structure. A dry gas seal (14) is provided in the high-pressure sealing casing (35). The high-pressure sealing casing (35) passes a dry gas seal ( 14) Connected to the rotor (23), the low-temperature carbon dioxide gas source is connected to the interior of the high-pressure sealed casing (35) through pipelines. The inner hole of the high-pressure insulated casing is provided with high-pressure end sealing teeth (333). The high-pressure end seal The teeth (333) fit with the outer circumference of the high-pressure impeller sleeve. A number of high-pressure guide vanes (331) are arranged on the upper circumference of the high-pressure insulated casing. Several high-pressure guide vanes (331) are located on the high-pressure centripetal impeller (32). On the outer air intake channel.
A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake according to claim 1, characterized in that: several low-pressure guide vanes (131) are integrally formed with the low-pressure heat-insulating casing (13), and several The tops of the low-pressure guide vanes (131) are connected through the first annular shroud (132). The low-pressure volute (11) is provided with a first annular groove, and the first annular shroud (132) is in contact with the first annular groove. Matching, several high-pressure guide vanes (331) are integrally formed with the high-pressure heat-insulating casing, the tops of several high-pressure guide vanes (331) are connected through the second annular shroud (332), and the high-pressure volute (31) is provided with The second annular groove, the second annular shroud (332) matches the second annular groove.
A supercritical carbon dioxide centripetal turbine structure suitable for 600°C air intake according to claim 1, characterized in that: the inner cavity wall of the low-pressure volute (11) is provided with a first abradable coating (111) , the first abradable coating (111) is provided in the matching gap area between the low-pressure volute (11) and the low-pressure radial impeller (12), and the second abradable coating is provided on the inner cavity wall of the high-pressure volute (31). layer (311), the second abradable coating (311) is located in the matching gap area between the high-pressure volute (31) and the high-pressure radial impeller (32).
A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake according to claim 1, characterized in that: a low-pressure bracket (17) is provided below the low-pressure volute (11), and the high-pressure volute (31) There is a high-voltage bracket (37) underneath.
A supercritical carbon dioxide centripetal turbine structure suitable for 600°C air intake according to claim 4, characterized in that: a heat insulation pad (19) is provided between the low-pressure volute (11) and the low-pressure bracket (17) , a heat insulation pad (19) is provided between the high-pressure volute (31) and the high-pressure bracket (37).
A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake according to claim 5, characterized in that: the circumferential direction of the low-pressure volute (11) passes through the first guide key (16) and the low-pressure bracket (17) ), the circumferential direction of the high-pressure volute (31) is matched with the high-pressure bracket (37) through the second guide key (36).
A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake according to claim 1, characterized in that: the high-pressure volute (31) and the high-pressure heat-insulating casing are sealed by a C-type sealing ring, The low-pressure volute (11) and the low-pressure heat-insulated casing (13) are sealed by a C-shaped sealing ring.
A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake according to claim 1, characterized in that: the bearing (24) is a tilting pad bearing (24).
A supercritical carbon dioxide centripetal turbine structure suitable for 600°C air intake according to claim 1, characterized in that: the rotation speed of the rotor (23) is 32000 r/min.
A supercritical carbon dioxide centripetal turbine structure adapted to 600°C air intake according to any one of claims 1 to 9, characterized in that: the high-pressure sealed casing (35) is a GH4169 material casing, and the high-pressure heat insulation machine The casing is made of GH4169 material, the high-pressure radial impeller (32) is made of GH4169 material, the high-pressure volute (31) is made of GH4169 material, the low-pressure sealed casing (15) is made of GH4169 material, and the low-pressure heat-insulated casing ( 13) is a casing made of GH4169 material, the low-pressure radial impeller (12) is made of GH4169 material, and the low-pressure volute (11) is a volute made of GH4169 material.