Low temperature turbine pump high temperature gas outlet end connection structure
阅读说明:本技术 一种低温涡轮泵高温燃气出口端连接结构 (Low temperature turbine pump high temperature gas outlet end connection structure ) 是由 毛凯 王晓锋 李春乐 张鹏飞 李昌奂 袁伟为 安康 于 2019-10-23 设计创作,主要内容包括:本发明涉及液体火箭发动机涡轮泵领域,提供一种低温涡轮泵高温燃气出口端连接结构,包括高温燃气出口管、低温壳体,低温壳体通过涡轮端轴承安装在转轴上,涡轮转子固定在转轴上,高温燃气出口管包括出口法兰、过渡段、小端、集气管和大端,在集气管的内表面周向设置导流支板;出口法兰、过渡段、小端、导流支板、集气管和大端为一体成型,采用高温合金材料制成;大端与小端分别设置在集气管上相对的两侧;高温燃气出口管与低温壳体通过螺母和螺栓连接;通过对高温燃气出口管内部型面进行三维优化,保证了高温燃气出口管流通顺畅且损失极小,提高了涡轮泵做功能力和涡轮泵效率。(The invention relates to the field of liquid rocket engine turbopumps, and provides a high-temperature gas outlet end connecting structure of a low-temperature turbopump, which comprises a high-temperature gas outlet pipe and a low-temperature shell, wherein the low-temperature shell is arranged on a rotating shaft through a turbine end bearing, a turbine rotor is fixed on the rotating shaft, the high-temperature gas outlet pipe comprises an outlet flange, a transition section, a small end, a gas collecting pipe and a large end, and a flow guide supporting plate is circumferentially arranged on the inner surface of the gas collecting pipe; the outlet flange, the transition section, the small end, the flow guide support plate, the gas collecting pipe and the large end are integrally formed and made of high-temperature alloy materials; the large end and the small end are respectively arranged on two opposite sides of the gas collecting pipe; the high-temperature gas outlet pipe is connected with the low-temperature shell through a nut and a bolt; by three-dimensionally optimizing the inner molded surface of the high-temperature gas outlet pipe, smooth circulation and extremely low loss of the high-temperature gas outlet pipe are ensured, and the work capacity and the efficiency of the turbopump are improved.)
1. The utility model provides a low temperature turbine pump high temperature gas outlet end connection structure, includes high temperature gas outlet pipe (7), low temperature casing (3), its characterized in that: the low-temperature shell (3) is mounted on a rotating shaft (1) through a turbine end bearing (2), a turbine rotor (9) is fixed on the rotating shaft (1), the high-temperature gas outlet pipe (7) comprises an outlet flange (71), a transition section (72), a small end (73), a gas collecting pipe (75) and a large end (76), a flow guide support plate (74) is circumferentially arranged on the inner surface of the gas collecting pipe (75), and the inner cavity sectional area of the gas collecting pipe (75) is gradually increased along the outlet direction; the transition section (72) is used for connecting the gas collecting pipe (75) with the outlet flange (71) in a smooth transition way; the outlet flange (71), the transition section (72), the small end (73), the flow guide support plate (74), the gas collecting pipe (75) and the large end (76) are integrally formed; the large end (76) and the small end (73) are respectively arranged on two opposite sides of the gas collecting pipe (75); and the high-temperature fuel gas outlet pipe (7) is connected with the low-temperature shell (3) through a nut (4) and a bolt (5).
2. The high-temperature gas outlet end connecting structure of the low-temperature turbine pump as claimed in claim 1, wherein: the guide support plate (74) is a straight blade with a uniform-section blade profile stretched along the circumferential direction, the large end (76) is connected with the small end (73), and the blade profile and the installation angle of the guide support plate (74) are obtained through three-dimensional flow field simulation software.
3. The high-temperature gas outlet end connecting structure of the low-temperature turbo pump according to claim 1 or 2, wherein: and a corner of the inner surface of the small end (73) is provided with a rounded corner R.
4. The high-temperature gas outlet end connecting structure of the low-temperature turbo pump as claimed in claim 3, wherein: and a labyrinth type sealing structure I (77) is arranged on the matching surface of the small end (73) and the turbine rotor (9).
5. The high-temperature gas outlet end connecting structure of the low-temperature turbo pump as claimed in claim 3, wherein: a labyrinth type sealing structure II (31) is arranged on the surface of an inner hole of the low-temperature shell (3) matched with the rotating shaft (1).
6. The high-temperature gas outlet end connecting structure of the low-temperature turbine pump as claimed in claim 5, wherein: and the area on the rotating shaft (1) matched with the labyrinth type sealing structure II (31) of the low-temperature shell (3) is treated by a silver plating process.
7. The high-temperature gas outlet end connecting structure of the low-temperature turbine pump as claimed in claim 1, wherein: the low-temperature shell (3) and the high-temperature gas outlet pipe (7) are sealed by a high-temperature sealing gasket (6), and the high-temperature sealing gasket (6) is made of brass materials.
8. The high-temperature gas outlet end connecting structure of the low-temperature turbine pump as claimed in claim 1, wherein: the low-temperature shell is characterized by further comprising a flow guide cone, wherein the flow guide cone is of a rotary structure and comprises a connected arc section (81) and a connected straight section (82), and an isolation cavity (10) is formed between the flow guide cone and the low-temperature shell (3).
9. The high-temperature gas outlet end connecting structure of the low-temperature turbo pump as claimed in claim 8, wherein: the flow guide cone is made of high-temperature alloy materials and is in threaded connection with the low-temperature shell (3).
10. The high-temperature gas outlet end connecting structure of the low-temperature turbo pump as claimed in claim 8, wherein: the surfaces of the diversion cone and the turbine rotor (9) and the inner cavity of the high-temperature gas outlet pipe (7) are coated with high-temperature-resistant thermal barrier coatings.
Technical Field
The invention belongs to the field of turbopumps of liquid rocket engines, and particularly relates to a high-temperature gas outlet end assembly structure of a low-temperature turbopump of a rocket engine.
Background
The turbopump is one of the key components in the liquid rocket engine, and is generally driven by a high-temperature gas turbine due to the very high power of the turbopump. Particularly for a afterburning cycle engine, the temperature of high-temperature gas needs to be reduced as much as possible on the premise of ensuring the performance of the engine so as to ensure the reliability of a high-temperature gas path of the engine, the efficiency of the turbine pump is directly related to the temperature of the high-temperature gas, and system adjustment and calculation show that the temperature of the high-temperature gas can be reduced by 10K when the efficiency of the turbine pump is improved by 1 percent, so that the design of a high-efficiency turbine assembly is very important. For the subsonic turbine, the influence of the structural design of the high-temperature gas outlet pipe of the turbine on the efficiency of the turbine pump is very large.
In addition, in the more advanced liquid oxygen kerosene engine turbine oxygen pump, the medium at the pump end is ultra-low temperature liquid oxygen, the temperature of the ultra-low temperature liquid oxygen is as low as minus 183 ℃, the turbine end is high temperature oxygen-enriched high temperature fuel gas, and the temperature of the turbine end is as high as 500 ℃. Generally, in order to ensure simple and compact structure, the pump and the turbine are designed coaxially, and the high-temperature gas outlet end of the turbine is directly connected with the low-temperature shell of the pump, which can cause temperature difference stress and deformation of relevant connecting parts due to extremely large temperature difference. Therefore, in order to ensure the operational reliability of the turbo pump, it is important to ensure the isolation between the low-temperature liquid medium and the high-temperature combustion gas, and to reduce the temperature difference stress and deformation of the related parts due to the extreme temperature difference.
Aiming at the two problems, in order to ensure the reliability of a high-temperature gas path of the engine, the structure of a high-temperature gas outlet end assembly needs to be optimally designed for improving the efficiency of a turbopump during the design of the engine, and the temperature difference stress and the deformation of parts need to be reasonably designed on the other hand.
Disclosure of Invention
The technical problem solved by the invention is as follows: the utility model provides a low temperature turbopump high temperature gas outlet end connection structure for the turbine has solved the temperature difference between low temperature part and the high temperature part when having higher efficiency and has greatly led to the problem of part deformation, thereby guarantees the reliability of high temperature gas way.
The basic concept of the invention is as follows: the 3D printing technology is combined, the structure and the internal molded surface of the high-temperature gas outlet pipe are optimized, smooth circulation of the high-temperature gas outlet pipe is guaranteed, loss is extremely low, and therefore the work capacity of the turbine and the efficiency of the turbine pump are improved. Meanwhile, the connecting structure of the warm gas outlet pipe and the low-temperature shell is optimized, a diversion cone part is arranged in the turbine outlet pipe, on one hand, the high-temperature gas at the outlet of the turbine rotor is smoothly guided into the gas collecting pipe of the turbine outlet pipe, on the other hand, the diversion cone isolates the high-temperature gas from the low-temperature shell, a relatively closed isolation cavity with a relatively large area is formed, the temperature in the isolation cavity is between the low-temperature liquid oxygen and the high-temperature gas, and the problem that the component is deformed due to the rapid change of the temperature gradient between the low-temperature component and the high-temperature component is solved due to the existence of the. The working reliability of the gas path of the turbopump is ensured by optimizing the two aspects.
The technical solution of the invention is as follows: the high-temperature gas outlet end connecting structure of the low-temperature turbine pump comprises a high-temperature gas outlet pipe and a low-temperature shell, wherein the low-temperature shell is arranged on a rotating shaft through a turbine end bearing, a turbine rotor is fixed on the rotating shaft, the high-temperature gas outlet pipe comprises an outlet flange, a transition section, a small end, a gas collecting pipe and a large end, a flow guide support plate is circumferentially arranged on the inner surface of the gas collecting pipe, the sectional area of an inner cavity of the gas collecting pipe is increased along the outlet direction, and the gas collecting pipe and the outlet flange are in smooth transition connection; the outlet flange, the transition section, the small end, the flow guide support plate, the gas collecting pipe and the large end are integrally formed and are made of high-temperature alloy materials by a 3D printing method; the large end and the small end are respectively arranged on two opposite sides of the gas collecting pipe; the high-temperature gas outlet pipe is connected with the low-temperature shell through a nut and a bolt; by three-dimensionally optimizing the inner molded surface of the high-temperature gas outlet pipe, smooth circulation and extremely low loss of the high-temperature gas outlet pipe are ensured, and the work capacity and the efficiency of the turbopump are improved.
Furthermore, the guide support plate is a straight blade with a uniform cross section and a blade profile stretched along the circumferential direction, the large end is connected with the small end, and the guide support plate is arranged to guide high-temperature gas at the outlet of the turbine into the gas collecting pipe on one hand, increase the strength and rigidity of the gas collecting pipe on the other hand and prevent the gas collecting pipe from excessively deforming under a high-pressure environment; the blade profile and the installation angle of the flow guide support plate are different, and the relevant parameters of the blade profile and the installation angle are obtained by optimizing three-dimensional flow field simulation software, so that the flow guide support plate can guide flow and generate minimum flow loss on the premise of meeting the requirements on strength and rigidity.
Furthermore, in order to reduce the energy loss of the gas at the outlet pipe of the turbine, the corner of the inner surface of the small end is provided with the fillet R, the high-temperature gas flow at the outlet of the turbine rotor smoothly transits into the gas collecting pipe, the energy loss of the high-temperature gas flowing through the small end is reduced, and the turbine efficiency is improved.
Furthermore, a labyrinth type sealing structure I is arranged on the matching surface of the small end and the turbine rotor, so that the leakage rate of high-temperature gas in the top clearance of the turbine is reduced, and the efficiency of the turbine pump is improved.
Further, because there is liquid oxygen to leak to high temperature gas chamber from low temperature liquid oxygen chamber always in the turbo pump working process, in order to reduce the leakage quantity in liquid oxygen chamber to high temperature gas chamber, be provided with labyrinth type seal structure II on low temperature casing and pivot complex hole surface, and then improve turbo pump efficiency.
Further, in order to reduce the collision and abrasion risk of the low-temperature shell and the rotating shaft, the region, matched with the labyrinth type sealing structure II of the low-temperature shell, on the rotating shaft is treated by a silver plating process.
Furthermore, a high-temperature sealing gasket is adopted for sealing between the low-temperature shell and the high-temperature gas outlet pipe, and the high-temperature sealing gasket is made of brass materials, so that the reliable connection between the low-temperature shell and the high-temperature gas outlet pipe is ensured.
The gas collecting pipe is characterized by further comprising a flow guide cone, wherein the flow guide cone is of a rotary structure and comprises a circular arc section and a straight line section which are connected, the flow guide cone smoothly transfers high-temperature gas into the gas collecting pipe and separates the high-temperature gas from the low-temperature shell, a closed isolation cavity is formed between the low-temperature shell and the high-temperature gas cavity, the temperature difference stress and deformation of the low-temperature shell are reduced, and the safe and reliable operation of the gas collecting pipe is guaranteed.
Furthermore, the diversion cone is made of high-temperature alloy materials through a forging machine and is in threaded connection with the low-temperature shell, and the diversion cone is convenient to mount.
Further, in order to improve the working safety of the component under the high-temperature oxygen-enriched gas, the surface of the guide cone which is directly contacted with the gas, the surface of the turbine rotor and the inner cavity of the high-temperature gas outlet pipe are coated with high-temperature-resistant thermal barrier coatings.
Compared with the prior art, the invention has the beneficial effects that:
1. the outlet flange, the transition section, the gas collecting pipe, the large end, the small end and the flow guide support plate of the high-temperature gas outlet pipe of the turbine are integrally formed, so that the connection among all the parts is in smooth transition, and the problems of thermal deformation and low precision caused by the traditional welding mode are solved.
2. The molded surface of the gas collecting pipe is subjected to three-dimensional modeling and optimization by combining a 3D printing preparation method, the molded surface of the gas collecting pipe is designed to have the trend that the sectional area of an inner cavity is increased along the outlet direction, and the gas collecting pipe is in smooth transition connection with the outlet flange by adopting a transition section, so that smooth gas circulation in the gas outlet pipe is ensured, and the work capacity of the turbine is improved.
3. The high-temperature gas outlet pipe is internally provided with the flow guide support plate, and the installation angle and the blade profile of the flow guide support plate are optimized by flow field simulation software, so that the high-temperature gas at the outlet of the turbine can be smoothly guided into the gas collecting pipe, the integral strength and rigidity of the high-temperature gas outlet are improved, and the working reliability of the high-temperature gas outlet pipe is improved.
4. Labyrinth seal structures are arranged at the inner hole of the large end of the high-temperature gas outlet pipe and the surface of the inner hole of the low-temperature shell, so that the leakage of liquid oxygen to the gap between the turbine end and the top of the turbine rotor is reduced, and the efficiency of the turbine pump is further improved.
5. Set up the water conservancy diversion awl between low temperature casing and high temperature gas outlet pipe, the water conservancy diversion awl can be smoothly with turbine rotor export high temperature gas water conservancy diversion to outlet pipe gas collection chamber, simultaneously, the water conservancy diversion awl keeps apart high temperature gas chamber and low temperature casing, has reduced the difference in temperature of low temperature casing, has reduced temperature stress and deformation to improve the holistic operational reliability of turbine.
6. In order to reduce the collision and abrasion risk of the low-temperature shell and the rotating shaft, a silver plating process is added in the rotating shaft in the area matched with the labyrinth type sealing structure II of the low-temperature shell, and in order to improve the working safety of high-temperature components under oxygen-enriched high-temperature gas, high-temperature-resistant thermal barrier coatings are coated on the surface of the flow guide cone, the surface of the turbine rotor and the inner cavity of the high-temperature gas outlet pipe, so that the integral working reliability of the turbine pump is further improved.
Drawings
FIG. 1 is a schematic view of the connection structure of the high-temperature gas outlet end of the low-temperature turbine pump of the invention;
FIG. 2 is a cross-sectional view of the high temperature gas outlet pipe A-A of FIG. 1;
FIG. 3 is a perspective view of the high temperature gas outlet pipe of FIG. 1;
FIG. 4 is a schematic structural diagram of a labyrinth type seal structure II of the present invention;
fig. 5 is an enlarged view of a portion B in fig. 1.
Reference numerals: the turbine comprises a
Detailed Description
The working mode of the afterburning cycle engine is as follows: after the fuel and the oxidant are pressurized by the pump, the fuel with small flow and the oxidant with full flow are separated to enter the precombustion chamber, high-temperature and high-pressure oxygen-enriched gas is generated by combustion in the precombustion chamber and is used for driving the main turbine to work, and the oxygen-enriched gas enters the main combustion chamber through a pipeline behind the turbine, is converged and fully combusted with most of the fuel behind the pump at the main combustion chamber and is discharged from the spray pipe. The invention optimizes the structure of the high-temperature gas outlet pipe to improve the efficiency of the turbine pump based on the concept of improving the efficiency of the turbine pump to reduce the temperature of high-temperature gas so as to ensure the reliability of the overall work of the turbine pump, and simultaneously optimizes the structure of a connecting component of the high-temperature gas outlet pipe and the turbine, wherein the structure comprises a diversion cone for isolating a high-temperature gas cavity and a low-temperature shell, so that the reliability of the connection and the work of the components of the turbine and the components of the high-temperature gas outlet pipe is improved, and the reliability of the overall work of the turbine is improved from.
Specifically, as shown in fig. 1 to 3, the high-temperature gas outlet end connecting structure of the low-temperature turbine pump of the invention comprises a rotating
As shown in fig. 2 and 3, the high-temperature
A plurality of
As shown in fig. 1 and 4, in order to further improve the efficiency of the turbine pump, a labyrinth type sealing structure i 77 is arranged on a matching surface of the
In order to ensure the working reliability of the turbine, as shown in fig. 1, a diversion cone is arranged between the low-temperature shell and the high-temperature gas outlet pipe, is made of high-temperature alloy materials by adopting a forging machine, and is in threaded connection with the low-
Specifically, the diversion cone is a revolving body structure, and specifically comprises a
In order to further ensure the working reliability of the turbine, the surface of the guide cone, the surface of the
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
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