Novel turbine interstage guide vane and aeroengine having the same

Abstract

The application discloses a novel turbine interstage guide vane and an aero-engine with the same, which comprises a guide vane, a force transmission frame, a bearing seat, a turbine casing, and a plurality of pipes. The bearing seat is arranged in the guide vane, the force transmission frame is arranged outside the guide vane, the turbine casing is arranged outside the force transmission frame and is fixedly connected with one end of the force transmission frame, and the guide vane is separately arranged to be not directly connected with the bearing seat and the force transmission frame, thereby mainly being used for bearing a gas temperature load. The force transmission frame comprises a force transmission cylinder sleeved outside the guide vane and a plurality of branch pipes, and the plurality of branch pipes are respectively radially arranged through the guide vane and are fixedly connected with the bearing seat. The plurality of pipes are respectively arranged in the plurality of branch pipes, and the pipes are respectively extended out of the force transmission cylinder to be connected with external supply pipelines, and the inner ends of the pipes are connected with the bearing seat. The guide vane can reduce the manufacturing cost, guarantee excellent high-temperature resistance and mechanical properties, and has a compact overall structure, thereby meeting the requirements of high power-weight ratio / push-weight ratio of the aero-engine.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a novel turbine-stage guide. Furthermore, this invention also relates to an aero-engine including the aforementioned novel turbine-stage guide. Background Technology

[0002] There are generally two types of pivot point arrangements for aero-engine cores: 1-1-0 and 1-0-1. When the engine core adopts a 1-0-1 pivot point layout, a bearing is placed behind the gas turbine. A force transmission frame must be installed between the gas turbine and the power turbine / low-pressure turbine to support the bearing. Branch pipes must be installed on the force transmission frame to transmit force. Behind this frame is the power / low-pressure turbine first-stage guide vane. The gas first passes through the force transmission frame and then enters the power / low-pressure turbine first-stage guide vane, as shown in the attached diagram. Figure 1 As shown.

[0003] Early designs of this type of engine resulted in greater length and weight. However, with engine development, weight reduction became a necessity to meet demands such as increased aircraft payload. Integrating the load-bearing frame and the power / low-pressure turbine guide vanes into an interstage guide vane became an effective means of weight reduction, but it also increased design complexity, as shown in the attached diagram. Figure 2 As shown:

[0004] The interstage guide vane is mounted on the turbine casing via bolts / stops and other connection structures, while the turbine bearing housing is also mounted in the interstage guide vane via bolts / stops and other connection structures. The turbine bearing is located below the turbine bearing housing. During engine operation, the combustion gas from the high-pressure turbine flows to the low-pressure turbine through the channel formed by the upper and lower flow channels of the interstage guide vane and the branch pipe / low-pressure turbine guide vanes. Therefore, during operation, the interstage guide vane is subjected to both high temperatures and mechanical loads transmitted from the rotor through the bearings, making its working environment extremely harsh.

[0005] The initial interstage guide adopted an integral casting scheme, which was compact and facilitated weight reduction. However, with the improvement of gas stability, the strength and life of the interstage guide could not meet the requirements due to the limitations of existing materials. Therefore, a new structural scheme needed to be redesigned. Summary of the Invention

[0006] This invention provides a novel turbine stage guide and an aero-engine incorporating the same, to solve the technical problem that existing integrated stage guide structures are limited by existing materials and cannot meet the requirements for strength, lifespan and compactness.

[0007] The technical solution adopted in this invention is as follows:

[0008] A novel turbine stage guide includes: a hollow annular guide, a force transmission frame, a bearing housing, and a turbine casing, as well as multiple conduits for guiding oil or gas. The bearing housing is coaxially mounted in the inner channel of the guide, the force transmission frame is coaxially mounted outside the guide, and the turbine casing is coaxially mounted outside the force transmission frame, with one end of the turbine casing fixedly connected to the force transmission frame along the axial direction. The guide is set separately so as not to be directly connected to the bearing housing and the force transmission frame, and is mainly used to bear the gas temperature load. The force transmission frame includes a hollow cylindrical force transmission cylinder fitted outside the guide, and multiple branch pipes arranged sequentially at intervals along the circumference of the force transmission cylinder, with the outer ends connected to the inner surface of the force transmission cylinder. The inner ends of the multiple branch pipes are respectively radially inserted through the guide and fixedly connected to the bearing housing. The multiple conduits are arranged one by one in the multiple branch pipes, and the outer ends of each conduit extend out of the force transmission cylinder to connect to the external oil or gas supply pipeline. The inner ends of each conduit are fixedly connected to the bearing housing.

[0009] Furthermore, the guide includes a coaxial inner guide cylinder and an outer guide cylinder spaced apart from each other, and multiple guide blades spaced apart along the circumference and connected between the inner guide cylinder and the outer guide cylinder; multiple branch pipes are arranged one-to-one with the multiple guide blades, and each branch pipe passes through the guide blade at the corresponding position in the radial direction and is then connected to the bearing seat.

[0010] Furthermore, the guide is formed by alternatingly welding together multiple blade basin segments and blade back segments that are broken off at each guide blade along the circumference; each blade basin segment includes a first lower edge plate and a first upper edge plate that are spaced apart from each other, and a blade basin of a guide blade connected between the two; each blade back segment includes a second lower edge plate and a second upper edge plate that are spaced apart from each other, and a blade back of a guide blade connected between the two; multiple first lower edge plates and second lower edge plates that are alternating along the circumference are sequentially welded together to form an inner guide cylinder; multiple first upper edge plates and second upper edge plates that are alternating along the circumference are sequentially welded together to form an outer guide cylinder.

[0011] Furthermore, the force transmission cylinder includes a rear turbine casing, a transition connecting ring, and an expansion ring groove ring arranged sequentially and welded together along the axial direction; the rear end of the rear turbine casing is used for disassembly and connection with the parts at the rear of the turbine, and the rear end of the turbine casing is welded to the outer ring surface of the rear turbine casing; multiple branch pipes are located in the inner channel of the force transmission cylinder, and the outer ends of each branch pipe are welded to the inner ring surface of the transition connecting ring, and the channel between the force transmission cylinder and the turbine casing is connected through a connecting port opened at the corresponding position on the transition connecting ring.

[0012] Furthermore, the rear turbine casing includes a hollow annular casing body, a flange connected to the rear end of the casing body, and an interface ring connected to the outer annular surface of the casing body; a transition connecting ring is welded to the inner end of the casing body along the axial direction; the flange is used to connect parts at the rear of the turbine; and the interface ring is welded to the rear end of the turbine casing.

[0013] Furthermore, the transition connecting ring is formed by welding together multiple intermediate sections and multiple support plate sections arranged alternately along the circumference. The support plate section includes a support plate that is welded to the rear turbine casing and the expansion ring groove ring at both ends respectively. The outer side of the support pipe is smoothly connected to the inner side of the support plate along the radial direction, and the bottom end of the support pipe has a welding surface for welding and fixing with the bearing seat. The rear turbine casing and the expansion ring groove ring are integrally formed.

[0014] Furthermore, the outer guide cylinder is machined with a plurality of first pin holes that are spaced apart circumferentially and penetrate the cylinder surface; the transition connecting ring is machined with a plurality of second pin holes that correspond one-to-one with the plurality of first pin holes; the new turbine stage guide also includes a plurality of positioning pins, each positioning pin being inserted into the corresponding first pin hole and second pin hole to position the guide.

[0015] Furthermore, the conduit is integrally formed, including a connecting port, a transition section, a middle section, and a bottom socket arranged sequentially along the axial direction; the connecting port is used for detachable connection with an external supply pipeline; the cross-section of the branch pipe is adapted to the cross-sectional shape at the corresponding height on the guide vane, and the cross-sections of the middle section and the bottom socket are adapted to the cross-sectional shapes at the corresponding height on the branch pipe, respectively; the bottom socket is used to insert into the bearing seat and weld it to the bearing seat for fixation.

[0016] Furthermore, the bearing housing is integrally formed, including a right stop, a bearing housing body, and a left stop arranged sequentially and welded together along the axial direction, as well as multiple mounting stops fixed at intervals on the outer ring surface of the bearing housing body, multiple oil passages connected at intervals on the outer ring surface of the bearing housing body, and air system passages arranged at intervals on the stop surface of the left stop; each mounting stop includes an integrally formed branch pipe welding port and a conduit welding port for connecting and welding to the corresponding branch pipe and conduit.

[0017] According to another aspect of the invention, an aircraft engine is also provided having a novel turbine-stage guide as described above.

[0018] The present invention has the following beneficial effects:

[0019] In the novel turbine stage guide of the present invention, such as Figure 3-4As shown, the guide is set up separately and is not directly connected to the bearing housing and force transmission frame. This allows the guide to be made of materials with excellent high-temperature resistance but low mechanical performance requirements, making it mainly used to bear the gas temperature load, thereby reducing manufacturing costs and ensuring excellent high-temperature resistance. At the same time, the separate setting of the guide can also effectively reduce the difficulty of manufacturing and assembly, and ensure the quality of parts. On the other hand, the turbine casing, force transmission frame, duct and bearing housing are fixed together to form an integral structure, which is used to ultimately transfer the mechanical load borne by the bearing housing to the engine outer casing connected to the turbine casing. Thus, this integral structure is mainly used for bearing and transmitting mechanical loads. At this time, the integral structure can be made of materials with excellent mechanical properties but low high-temperature resistance requirements, ensuring its excellent mechanical properties, while also effectively reducing the high cost required for high-temperature resistant materials. In addition, the turbine casing, force transmission frame, duct and bearing housing are interwoven and connected to form an integral structure, and the guide is also arranged in this integral structure, so that the overall structure of the new turbine stage guide is compact and meets the requirements of high power-to-weight ratio / thrust-to-weight ratio of aero engines.

[0020] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0021] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0022] Figure 1 This is a structural diagram of an existing turboshaft engine;

[0023] Figure 2 This is a schematic diagram of an existing integrated interstage guide structure;

[0024] Figure 3 This is a first cross-sectional main view of the novel turbine stage guide according to a preferred embodiment of the present invention;

[0025] Figure 4 This is a second cross-sectional main view of the novel turbine stage guide according to a preferred embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the guide space division;

[0027] Figure 6 yes Figure 5 Schematic diagram of the middle section;

[0028] Figure 7 This is a schematic diagram of the duct space structure;

[0029] Figure 8yes Figure 7 A top-view structural diagram;

[0030] Figure 9 yes Figure 7 A schematic diagram of the structure viewed from below;

[0031] Figure 10 This is a schematic diagram of the spatial structure of the force transmission frame;

[0032] Figure 11 yes Figure 10 A schematic diagram of a half-section structure;

[0033] Figure 12 yes Figure 11 The bending structure is shown in the figure;

[0034] Figure 13 This is a schematic diagram of the first spatial structure of the bearing housing;

[0035] Figure 14 This is a schematic diagram of the second space structure of the bearing housing.

[0036] Legend:

[0037] 1. Guide vane; 104. First expansion ring; 105. Second expansion ring; 11. Blade head section; 111. Blade head; 112. First upper edge plate; 113. First lower edge plate; 12. Blade back section; 121. Blade back; 122. Second upper edge plate; 123. Second lower edge plate; 124. First pin hole; 2. Force transmission frame; 21. Rear turbine casing; 211. Flange; 212. Interface ring; 22. Support plate section; 221. 222. Branch pipe; 223. Support plate; 223. Welding surface; 23. Intermediate section; 231. Second pin hole; 24. Expansion ring groove; 3. Bearing housing; 31. Conduit weld joint; 32. Branch pipe weld joint; 33. Right stop; 34. Left stop; 35. Lubricating oil passage; 36. Air system passage; 4. Conduit; 41. Connecting port; 42. Adapter section; 43. Intermediate section; 44. Bottom insertion port; 5. Locating pin; 6. Turbine casing. Detailed Implementation

[0038] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0039] Reference Figure 3-4A preferred embodiment of the present invention provides a novel turbine stage guide, comprising: a hollow annular guide 1, a force transmission frame 2, a bearing housing 3, and a turbine casing 6, as well as multiple conduits 4 for guiding oil or gas. The bearing housing 3 is coaxially mounted in the inner channel of the guide 1, the force transmission frame 2 is coaxially mounted outside the guide 1, and the turbine casing 6 is coaxially mounted outside the force transmission frame 2, with one end of the turbine casing 6 fixedly connected to the force transmission frame 2 along the axial direction. The guide 1 is separately configured so as not to be directly connected to the bearing housing 3 and the force transmission frame 2, and is mainly used to bear the gas temperature load. The force transmission frame 2 includes a hollow cylindrical force transmission cylinder fitted outside the guide 1, and multiple branch pipes 221 arranged sequentially at intervals along the circumference of the force transmission cylinder, with their outer ends connected to the inner surface of the force transmission cylinder. The inner ends of the multiple branch pipes 221 are respectively radially inserted through the guide 1 and fixedly connected to the bearing housing 3. Multiple conduits 4 are installed in multiple branch pipes 221, and the outer end of each conduit 4 extends out of the force transmission cylinder to connect to the external oil or gas supply pipeline. The inner end of each conduit 4 is fixedly connected to the bearing seat 3.

[0040] Many current aero engines, in pursuit of high power-to-weight ratios / thrust-to-weight ratios, require compact designs and increased turbine inlet temperatures. As temperatures rise, traditional... Figure 2 The integrated interstage guide shown is difficult to withstand both temperature and mechanical load requirements simultaneously. In the novel turbine interstage guide of this invention, as... Figure 3-4 As shown, the guide 1 is set separately and not directly connected to the bearing housing 3 and the force transmission frame 2. Therefore, the guide 1 can be made of a material with excellent high-temperature resistance and low mechanical performance requirements, so that it is mainly used to bear the gas temperature load, thereby reducing the manufacturing cost and ensuring excellent high-temperature resistance. At the same time, the separate setting of the guide 1 can also effectively reduce the difficulty of manufacturing and assembly, and ensure the quality of the parts. On the other hand, the turbine casing 6, the force transmission frame 2, the duct 3 and the bearing housing 3 are fixed together to form an integral structure, which is used to ultimately transfer the mechanical load borne by the bearing housing 3 to the engine outer casing connected to the turbine casing 6. Thus, this integral structure is mainly used for bearing and transmitting mechanical load. At this time, the integral structure can be made of a material with excellent mechanical properties and low high-temperature resistance requirements, ensuring its excellent mechanical properties, while also effectively reducing the high cost required for high-temperature resistant materials. In addition, the turbine casing 6, the force transmission frame 2, the duct 3 and the bearing housing 3 are interwoven and connected to form an integral structure. The guide is also arranged through this integral structure, so that the overall structure of the new turbine stage guide is compact and meets the requirements of high power-to-weight ratio / thrust-to-weight ratio of aero engines.

[0041] Optionally, such as Figure 3As shown, the guide 1 includes a coaxial inner guide cylinder and an outer guide cylinder spaced apart from each other, and multiple guide blades spaced apart circumferentially and connected between the inner and outer guide cylinders. Multiple branch pipes 221 are arranged one-to-one with the multiple guide blades, and each branch pipe 221 passes through the guide blade at the corresponding position radially and then connects to the bearing seat 3.

[0042] Preferably, such as Figure 5-6 As shown, the guide 1 is formed by alternating circumferential welding of multiple blade basin sections 11 and blade back sections 12, which are broken off along each guide blade. In this preferred embodiment, the multiple blade basin sections 11 and multiple blade back sections 12 are formed by breaking off the guide 1 along each guide blade. Therefore, during assembly, the circumferential branch pipes 221 can be laid out first, and then the adjacent blade basin sections 11 and blade back sections 12 can be welded. This structural design of the guide 1 facilitates the installation and laying out of the branch pipes 221. Moreover, the installation space at the guide 1 is compact, making it difficult to connect it into a whole using traditional bolts / nuts. However, the adjacent blade basin sections 11 and blade back sections 12 are welded together, which not only facilitates the connection operation and reduces the overall weight of the guide 1, but also provides the guide 1 with better strength and rigidity than traditional bolt / nut connections after welding.

[0043] Furthermore, such as Figure 5-6 As shown, each blade basin section 11 includes a first lower edge plate 113 and a first upper edge plate 112 spaced apart internally and externally, and a blade basin 111 for guide blades connected between the two. Each blade back section 12 includes a second lower edge plate 123 and a second upper edge plate 122 spaced apart internally and externally, and a blade back 121 for guide blades connected between the two. Multiple first lower edge plates 113 and second lower edge plates 123 arranged alternately in the circumferential direction are sequentially welded together to form a guide inner cylinder. Multiple first upper edge plates 112 and second upper edge plates 122 arranged alternately in the circumferential direction are sequentially welded together to form a guide outer cylinder. In a specific embodiment of this preferred solution, the guide 1 is made of a high-temperature resistant material, such as K447A material, and is sealed by a first expansion ring 104 installed in an annular groove at the front end of the first upper edge plate 112 and a second expansion ring 105 installed in an annular groove at the front end of the first lower edge plate 113. Sealing can also be achieved through structures such as grates and irregular metal rings.

[0044] Optionally, such as Figure 10-11As shown, the force transmission cylinder includes a rear turbine casing 21, a transition connecting ring, and an expansion ring groove ring 24, which are arranged sequentially and welded together along the axial direction. The rear end of the rear turbine casing 21 is used for detachable connection with parts at the rear of the turbine, and the rear end of the turbine casing 6 is welded to the outer ring surface of the rear turbine casing 21. Multiple branch pipes 221 are located in the inner channel of the force transmission cylinder, and the outer ends of each branch pipe 221 are welded to the inner ring surface of the transition connecting ring, and the channel between the force transmission cylinder and the turbine casing 6 is connected through a connecting port opened at a corresponding position on the transition connecting ring. During assembly, the transition connecting ring and guide 1 are assembled first, and then the rear turbine casing 21 and expansion ring groove 24 are welded to the transition connecting ring respectively. This structural setting of the force transmission cylinder facilitates the passage of the transition connecting ring through the guide 1, and the connection and fixation of the rear turbine casing 21, the transition connecting ring and the expansion ring groove 24. In addition, the installation space at the force transmission frame 2 is compact, making it difficult to connect it into a whole using traditional bolts / nuts. Welding not only facilitates the connection operation and reduces the overall weight of the force transmission frame 2, but also provides the force transmission cylinder with better strength and rigidity than traditional bolt / nut connections.

[0045] In this optional solution, such as Figure 11 As shown, the rear turbine casing 21 includes a hollow annular casing body, a flange 211 connected to the rear end of the casing body, and an interface ring 212 connected to the outer annular surface of the casing body. A transition connecting ring is welded to the inner end of the casing body along the axial direction. The flange 211 is used to connect parts at the rear of the turbine. The interface ring 212 is welded to the rear end of the turbine casing 6.

[0046] In this optional solution, such as Figure 10-12 As shown, the transition connecting ring is formed by sequentially welding together multiple intermediate segments 23 and multiple support plate segments 22 arranged alternately along the circumference. Each support plate segment 22 includes a support plate 222 whose two ends are respectively welded to the turbine casing 21 and the expansion ring groove 24. The outer radial end of the branch pipe 221 smoothly transitions to the inner surface of the support plate 222, and the bottom end of the branch pipe 221 has a welding surface 223 for welding and fixing to the bearing seat 3. Preferably, as shown... Figure 11 As shown, the support plate 222 and the support pipe 221 are integrally formed, and the force transmission cylinder is as follows: Figure 11 The bending structure shown has a temperature field between it, the turbine casing 6, and the bearing housing 3, which leads to inconsistent deformation. The bending structure allows the force transmission frame 2 to deform at this point to release deformation pressure, thereby reducing the stress on the parts and improving their strength and lifespan.

[0047] In this optional solution, the transition connecting ring is formed by welding together multiple intermediate sections 23 and multiple support plate sections 22 arranged alternately along the circumference. Thus, during assembly, the intermediate sections 23 and support plate sections 22 can be laid out first, and then the turbine casing 21 and expansion ring groove 24 can be welded. This structural design of the transition connecting ring facilitates the installation and layout of the branch pipe 221. Moreover, the installation space at the transition connecting ring is compact, making it difficult to connect it into a whole using traditional bolts / nuts. The adjacent intermediate sections 23 and support plate sections 22 are welded together, which not only facilitates the connection operation and reduces the overall weight of the transition connecting ring, but also provides the strength and rigidity of the transition connecting ring after welding that is superior to the traditional bolt / nut connection.

[0048] In this optional solution, such as Figure 11 As shown, since neither the rear turbine casing 21 nor the expansion ring groove 24 is connected to the guide 1, in this invention, the rear turbine casing 21 and the expansion ring groove 24 are integrally formed. If 3D printing technology is used for forming, the forming difficulty is reduced and the forming quality is improved.

[0049] Optionally, such as Figure 4 As shown, the guide outer cylinder is machined with multiple first pin holes 124 that are spaced apart circumferentially and penetrate the cylinder surface. The transition connecting ring is machined with multiple second pin holes 231 that correspond one-to-one with the multiple first pin holes 124. The new turbine stage guide also includes multiple positioning pins 5, each of which is inserted into the corresponding first pin hole 124 and second pin hole 231 to position the guide 1. Due to the significant temperature difference between the guide 1 and other parts, in order to ensure smooth assembly of the guide 1 without thermal mismatch, the guide 1 uses multiple positioning pins 5 that simultaneously penetrate the guide outer cylinder and the transition connecting ring for positioning / centering. In addition to positioning pins 5, grooves / boobs can also be used for positioning / centering.

[0050] Optionally, such as Figure 7-9As shown, the conduit 4 is integrally formed and includes a connection port 41, a transition section 42, a middle section 43, and a bottom inlet 44 arranged sequentially along the axial direction. The connection port 41 is used for detachable connection with an external supply pipeline. The cross-section of the branch pipe 221 is adapted to the cross-sectional shape at the corresponding height on the guide vane, and the cross-sections of the middle section 43 and the bottom inlet 44 are adapted to the cross-sectional shapes at the corresponding heights on the branch pipe 221, respectively. Therefore, compared with a circular cross-section, the cross-sectional arrangement of the branch pipe 221 and the conduit 4 can maximize the area of ​​the internal channels of the branch pipe 221 and the conduit 4, thereby increasing the flow rate of lubricating oil or gas. The bottom inlet 44 is used to insert into the bearing seat 3 and weld it to the bearing seat 3 for fixation. In this optional solution, the conduit 4 can be processed by 3D printing or by sheet metal processing. Its connection port 41 can be sealed to the external supply pipeline by thread / pipe fitting, O-ring, or special ring.

[0051] Optionally, such as Figure 13-14 As shown, the bearing housing 3 is integrally formed, including a right stop 33, a bearing housing body, and a left stop 34 that are sequentially arranged and welded together along the axial direction, as well as multiple mounting stops fixed at intervals on the outer ring surface of the bearing housing body, multiple oil channels 35 sequentially connected at intervals on the outer ring surface of the bearing housing body, and air system channels 36 sequentially arranged at intervals on the stop surface of the left stop 34. Each mounting stop includes an integrally formed branch pipe welding port 32 and a conduit welding port 31 for connecting and welding to the corresponding branch pipe 221 and conduit 4. In this optional solution, the bearing housing 3 is integrally formed without segmented welding, which improves the forming quality and reduces the manufacturing difficulty. Furthermore, the bearing housing 3 adopts an integrated structural design, such as integrating the oil channels 35 and air system channels 36 into the bearing housing body, which helps to reduce the number of parts and weight, and improve its operational reliability.

[0052] A preferred embodiment of the present invention also provides an aero-engine having a novel turbine-stage guide as described above. Thus, the aero-engine of the present invention can effectively reduce manufacturing costs, ensure excellent high-temperature resistance and mechanical properties, and also effectively reduce manufacturing and assembly difficulties, ensure component quality. Furthermore, the aero-engine of the present invention has a compact overall structure, meeting the requirements of a high power-to-weight ratio / thrust-to-weight ratio for aero-engines.

[0053] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A turbine inter-stage guide characterized in that, The utility model relates to a hollow ring guide (1), force transmission frame (2), bearing seat (3) and turbine casing (6) and a plurality of pipes (4) for guiding oil or gas. The bearing seat (3) is coaxially arranged in the inner passage of the guide (1), the force transmission frame (2) is coaxially arranged outside the guide (1), the turbine casing (6) is coaxially arranged outside the force transmission frame (2), and the turbine casing (6) is fixedly connected to the force transmission frame (2) at one end in the axial direction, the guide (1) is separately arranged and is not directly connected to the bearing seat (3) and the force transmission frame (2), thereby mainly used for bearing the gas temperature load. The force transmission frame (2) comprises a hollow cylindrical force transmission cylinder arranged outside the guide (1) and a plurality of branch pipes (221) arranged in the circumferential direction of the force transmission cylinder and fixedly connected to the inner cylinder surface of the force transmission cylinder, and the inner end of each branch pipe (221) is fixedly connected to the bearing seat (3) after penetrating the guide (1) in the radial direction. The plurality of pipes (4) are arranged in the plurality of branch pipes (221) one by one, and the outer end of each pipe (4) extends out of the force transmission cylinder to be connected to the oil supply or gas supply pipeline outside. The guide (1) comprises a guide inner cylinder and a guide outer cylinder arranged coaxially and spaced apart inside and outside, and a plurality of guide vanes arranged in the circumferential direction and connected between the guide inner cylinder and the guide outer cylinder, and the plurality of branch pipes (221) are arranged one by one corresponding to the plurality of guide vanes, and the branch pipe (221) is connected to the bearing seat (3) after penetrating the corresponding guide vane in the radial direction. The guide (1) is formed by alternately welding a plurality of vane basin segments (11) and vane back segments (12) formed by cutting along each guide vane in the circumferential direction, each vane basin segment (11) comprises a first lower edge plate (113) and a first upper edge plate (112) arranged spaced apart inside and outside, and a vane basin (111) of the guide vane connected between the two, and each vane back segment (12) comprises a second lower edge plate (123) and a second upper edge plate (122) arranged spaced apart inside and outside, and a vane back (121) of the guide vane connected between the two.

2. The turbine inter-stage guide according to claim 1, wherein the plurality of first lower edge plates (113) and second lower edge plates (123) arranged alternately in the circumferential direction are sequentially welded to form the guide inner cylinder.

3. The turbine inter-stage guide according to claim 1, wherein the force transmission cylinder comprises a rear turbine casing (21), a transition connecting ring and a ring groove ring (24) arranged sequentially in the axial direction and welded together. The rear side end of the rear turbine casing (21) is used for detachable connection with the parts at the rear of the turbine, and the rear side end of the turbine casing (6) is welded to the outer ring surface of the rear turbine casing (21). The plurality of branch pipes (221) are located in the inner passage of the force transmission cylinder, and the outer end of each branch pipe (221) is welded to the inner ring surface of the transition connecting ring and communicates the passage between the force transmission cylinder and the turbine casing (6) through the communication port formed in the corresponding position of the transition connecting ring. ​ ​ ​ ​ 4. The turbine inter-stage guide according to claim 3, characterized in that, the rear turbine casing (21) comprises a hollow annular casing body, a flange (211) connected to the rear end of the casing body, and an interface ring (212) connected to the outer surface of the casing body; the casing body is welded to the transition connecting ring at the inner end along the axial direction; the flange (211) is used to connect the rear part of the turbine; the interface ring (212) is welded to the rear end of the turbine casing (6).

5. The turbine inter-stage guide according to claim 3, characterized in that, the transition connecting ring is formed by welding a plurality of intermediate segments (23) and a plurality of support plate segments (22) arranged alternately along the circumferential direction in sequence, the support plate segment (22) comprises a support plate (222) welded to the rear turbine casing (21) and the expansion ring groove ring (24) at both ends; the support pipe (221) is smoothly connected to the inner side of the support plate (222) at the outer end along the radial direction, and the bottom end of the support pipe (221) has a welding surface (223) for welding with the bearing seat (3); the rear turbine casing (21) and the expansion ring groove ring (24) are integrally formed.

6. The turbine inter-stage guide according to claim 3, characterized in that, a plurality of first pin holes (124) are arranged on the guide outer cylinder, and the first pin holes (124) are arranged on the transition connecting ring in one-to-one correspondence; the turbine inter-stage guide further comprises a plurality of positioning pins (5), each of which is inserted into the corresponding first pin hole (124) and the second pin hole (231) to position the guide (1).

7. The turbine inter-stage guide according to claim 1, characterized in that, the guide pipe (4) is integrally formed and comprises a connecting port (41), a transition segment (42), a middle segment (43), and a bottom port (44) arranged along the axial direction in sequence; the connecting port (41) is used to detachably connect with an external supply pipeline; the cross section of the support pipe (221) is adapted to the cross section shape of the corresponding height of the guide vane, and the cross sections of the middle segment (43) and the bottom port (44) are respectively adapted to the cross section shape of the corresponding height of the support pipe (221); the bottom port (44) is used to be inserted into the bearing seat (3) and welded thereto.

8. The turbine inter-stage guide according to claim 1, characterized in that, the bearing seat (3) is integrally formed and comprises a right stop (33), a bearing seat body, and a left stop (34) arranged along the axial direction in sequence and welded together, a plurality of mounting stops arranged on the outer surface of the bearing seat body in sequence, a plurality of oil passages (35) connected to the outer surface of the bearing seat body in sequence, and an air system passage (36) arranged on the stop surface of the left stop (34) in sequence; each mounting stop comprises a support pipe welding port (32) and a guide pipe welding port (31) integrally arranged, and is used to connect and weld with the corresponding support pipe (221) and guide pipe (4). The turbine inter-stage guide according to any one of claims 1-8.

9. An aeroengine characterised in that, ​

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