A compact transition
By integrating the transition section, bearing housing, power turbine guide, and supply/return oil pipes into a single design, the problems of complex assembly, oil leakage, large flow loss, and excessive weight have been solved, resulting in a compact structure, lightweight design, and improved economy.
Patent Information
- Application Number
- CN202520244688.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-17
- Publication Date
- 2025-11-28
- Estimated Expiration
- 2035-02-17
AI Technical Summary
The transition section, bearing housing, power turbine guide vane, and oil supply/return pipe of existing small and medium-sized turboshaft and turboprop engines are separate structures, which leads to problems such as complicated assembly, poor sealing, oil leakage, large flow loss, excessive engine weight, and high cost.
The transition section, bearing housing, power turbine guide vane, and supply/return oil pipes are integrated into a single design, employing a one-piece molded structure. This includes a sealed inner cavity for the bearing housing and the transition section, external threaded connections for the supply/return oil pipes, and a dot matrix structure. Interface bolt connections are eliminated, and sealing rings and soft metal structures are added to achieve sealing and lightweighting.
It simplifies the assembly process, prevents oil leaks and metal shavings from entering, shortens the axial length of the engine, improves rigidity and assemblability, reduces the number of parts, lowers costs, and achieves lightweight design.
Smart Images
Figure CN223608597U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to a compact structure transition section and belongs to the technical field of airplane engine. BACKGROUND
[0002] The turbine of small and medium-sized turboshaft and turboprop engine can be divided into gas turbine and power turbine, which are used to drive the compressor and output shaft power respectively, and the structure between the gas turbine and the power turbine is called transition section, as shown in the figure. Figure 1 From the structure, the inner and outer walls of the transition section cross section form an airflow channel, and generally, there are four hollow support plates 1d evenly distributed at 12 o'clock, 3 o'clock, 6 o'clock and 9 o'clock to bridge the inner and outer flow channels, which play the role of load transmission and providing a channel for the oil supply and return pipe.(1) At present, the transition section, bearing seat 1a, power turbine guide 1b and oil supply and return pipe 1c of most engines are of separate structure, among which the power turbine guide and the bearing seat are connected to the flange of the transition section through bolts, and the oil supply and return pipe is connected to the interface of the bearing seat through threads, which has the following shortcomings: first, the transition section, power turbine guide, bearing seat and oil supply and return pipe are assembled into components respectively, and then further assembled into parts, which has more assembly process steps and a complex assembly process;(2) The oil supply and return pipe is connected to the interface of the bearing seat through threads, in order to improve the sealing effect, the head of the oil supply and return pipe is designed with a soft metal gasket, which needs to be frequently disassembled and assembled during the engine disassembly and inspection process, and the soft metal gasket is easy to wear and crack during the frequent disassembly and assembly process, which causes the interface to be not tightly sealed and leads to oil leakage, in addition, the metal chips caused by wear and cracking are easy to enter the lubricating oil system, which has the risk of damaging the bearing;(3) The gas first passes through the channel of the transition section, and then flows out through the power turbine guide, which has the disadvantage that the gas passes a long distance, increasing the flow loss and making the engine axial size longer and the weight overweight;(4) In order to seal the bearing seat, power turbine guide and transition section, a sealing ring needs to be additionally used, which increases the cost.
[0003] Therefore, it is necessary to improve the prior art to solve the problems of the prior art. UTILITY MODEL CONTENTS
[0004] The utility model provides a compact structure transition section to solve the problems of the prior art.
[0005] The utility model adopts the technical scheme of compact structure's transition section, which is integrally formed with bearing seat and power turbine guider, the transition section forms transition section support plate, the bearing seat is integrally formed with oil supply and return pipe, the right side of bearing seat is formed with positioning boss, the inner cylindrical surface, outer cylindrical surface and vertical wall surface of bearing seat respectively constitute inner stop structure and outer stop structure, the inner stop structure is installed with elastic support to realize the closure of bearing seat inner chamber and form oil chamber of bearing seat inner chamber, the outer stop structure is installed with sealing ring to realize the closure of transition section inner chamber and form cold gas chamber of transition section inner chamber, the transition section support plate and the guide blade on the power turbine guider are integrally formed together.
[0006] Further, the top of the oil supply and return pipe is formed with an external thread part, the transition section support plate is formed with a hollow inner chamber penetrating up and down, and the external thread part on the top of the oil supply and return pipe is located above the hollow inner chamber after penetrating through the hollow inner chamber.
[0007] Further, the bearing seat is formed with a bearing mounting structure, and the left side of the bearing mounting structure is mounted with a sealing ring structure.
[0008] Further, the sealing ring structure is welded with a soft metal structure.
[0009] Further, the part where the transition section is connected with the bearing seat is designed as a V-shaped structure.
[0010] Further, the transition section support plate and the guide blade are designed as a dot matrix structure.
[0011] Further, the dot matrix structure is a body-centered cubic structure, an edge structure, a body-centered cubic edge structure, or a face-centered cubic edge structure.
[0012] The utility model has the following beneficial effects:
[0013] (1) The oil supply and return pipe and the transition section are designed integrally, which solves the problem of oil leakage at the interface with the bearing seat due to frequent assembly and disassembly of the oil supply and return pipe, and also solves the problem of bearing damage caused by metal chips entering the oil system due to frequent disassembly of the oil supply and return pipe.
[0014] (2) The power turbine guider and the transition section are designed integrally, which can shorten the axial length of the engine, and solve the problem of inconvenient installation and maintenance of the engine in the limited space of the nacelle of the airplane.
[0015] (3) The bearing seat and the transition section are designed integrally, and the interface bolt connection structure is cancelled, which is beneficial to reduce the stiffness loss, can improve the rigidity of the whole engine, and is convenient for stable transmission of the bearing load to the outside.
[0016] (4) The transition section, power turbine guider, bearing seat and oil supply / return pipe are integrally formed, which greatly reduces the number of parts, and the reduction of the number of parts is very beneficial to improve the assembly, and can reduce the weight of the engine, which is beneficial to lightweight design, in addition, can reduce the machining cost and improve the economy. BRIEF DESCRIPTION OF DRAWINGS
[0017] Figure 1 Figure 1 is a schematic view of the prior art transition section, bearing seat, power turbine guider and oil supply / return pipe.
[0018] Figure 2 Figure 2 is a schematic view of the transition section, bearing seat, power turbine guider and oil supply / return pipe of the utility model.
[0019] Figure 3 Figure 3 is a schematic view of the transition section support plate and guide vane.
[0020] Figure 4 Figure 4 is an exploded view of the transition section support plate and guide vane. DETAILED DESCRIPTION
[0021] The utility model will be further described below with reference to the drawings.
[0022] The utility model discloses a compact structure transition section, which is integrally designed with bearing seat 2, and the bearing seat 2 is integrally formed with oil supply / return pipe 1 having an external thread part at the top, the right side of the bearing seat 2 is protruded to form positioning boss 3, and the cantilever of the bearing seat 2 is protruded to form bearing installation structure 4.
[0023] The transition section is formed with transition section support plate 10, which is formed with hollow inner cavity 100 penetrating from top to bottom, and the top of the oil supply / return pipe 1 is located above the hollow inner cavity 100 after penetrating through the hollow inner cavity. The bottom of the oil supply / return pipe 1 is integrally formed with the bearing seat 2. Since the top of the oil supply / return pipe 1 is processed with an external thread part, when oil supply or return is needed, the external pipeline can be directly connected through the thread part at the top. Since the thread part is on the outer layer of the transition section, the space is large, and the assembly and disassembly are very convenient. In addition, since the top of the oil supply / return pipe 1 is an external thread part, even if metal chips are generated due to friction during the fastening process with the external pipeline and other object parts, the metal chips will fall on the outer wall surface of the oil pipe and will not enter the bearing cavity, thereby avoiding the risk of bearing wear. The existing oil supply / return pipe and bearing seat are designed in a split manner, and the oil supply / return pipe 1 must first penetrate through the transition section support plate 10 and then be threadedly fastened with the bearing seat 2, which belongs to blind assembly, and sometimes the assembly of the oil supply / return pipe 1 may not be in place due to machining deviation. In the utility model, the oil supply / return pipe 1 is integrally formed with the bearing seat 2, which can effectively solve the above technical problems. According to actual needs, the oil supply / return pipe 1 can be two, three or four.
[0024] The right side of the bearing seat 2 is formed with a positioning boss 3, and the inner cylindrical surface 30 and the outer cylindrical surface 31 of the positioning boss 3 and the vertical wall surface 20 form L-shaped inner and outer stop structures (not marked) respectively. The elastic support and the sealing ring are precisely matched with the positioning boss 3 through the L-shaped inner and outer stop structures, and the bearing seat inner cavity a and the transition section inner cavity b can be closed respectively, so as to form the oil cavity of the bearing seat inner cavity and the cold gas cavity of the transition section inner cavity.
[0025] The bearing mounting structure 4 is internally designed with an oil path (not shown) and an oil hole (not shown) for lubricating the bearing 2. The left side of the bearing mounting structure 4 is mounted with a sealing ring structure 5. When the lubricating oil lubricates the bearing 2 through the oil hole, it will inevitably splash everywhere during high-speed rotation of the bearing, and the high oil temperature is easy to form oil gas. Therefore, two sealing ring structures 5 are installed on the left side, and soft metal structures 7 are welded on the sealing ring structures 5. Through the soft metal structures 7, the purpose of preventing oil gas leakage can be achieved. The remaining positions on the transition section are also welded with soft metal structures 7, which can seal the cold gas and prevent the cold gas from leaking. The inner diameter size of the bearing seat 2 is determined according to the oil cavity volume of the required bearing seat inner cavity. Under the condition of meeting other structure requirements, it should be as large as possible, so as to prevent the oil leakage phenomenon caused by the small oil cavity volume after the temporary oil return is not smooth.
[0026] The part where the transition section connects with the bearing seat 2 is designed as a V-shaped structure 6 to provide support for blank forming and solve the problem of collapse during blank forming. In addition, the gas inlet of the transition section is designed as a flared mouth structure 8 to prevent the formation of inverted steps affecting the gas flow field and thus affecting the performance of the engine.
[0027] The transition section support plate 10 and the guide vane 11 on the power turbine guide are integrally formed together, and the transition section support plate 10 and the guide vane 11 are designed as a dot matrix structure 9. After the power turbine guide and the transition section are designed as a whole, the gas first passes through the transition section support plate and then passes through the guide vane of the power turbine guide, and then it passes through the transition section support plate and the guide vane at the same time, that is, the guide vane and the transition section support plate change from the original series connection to a parallel structure. In this way, the axial length of the part can be shortened, and the gas flow loss can be reduced. On the other hand, when the parts are designed separately, the bearing load is transmitted by the transition section support plate. Now, after the integrated design, the bearing load can be borne by the transition section support plate and the guide vane together, which reduces the stress level of the transition section support plate and the guide vane. Therefore, the transition section support plate and the guide vane can be designed as a dot matrix structure. The dot matrix structure can be a body-centered cubic structure, an edge structure, a body-centered cubic edge structure, a face-centered cubic edge structure, etc. The dot matrix structure design can reduce the weight while ensuring the strength.
[0028] The utility model discloses compact transition section and power turbine guider, bearing seat 2 and supply / return oil pipe 1 integration forming. Will supply / return oil pipe 1 and transition section integration design, solved because supply / return oil pipe 1 frequent wear and tear of dismounting and lead to the oil leakage of bearing seat 2 interface place problem, also solved because supply / return oil pipe 1 frequent dismounting and lead to the bearing damage problem of metal scrap into the oil system. On the other hand, transition section, power turbine guider integration design can shorten the axial length of engine, improve compactness, solved the engine in the short cabin of aircraft space limited inconvenient installation, maintenance problem. In addition, transition section, bearing seat integration design can improve the rigidity of engine whole, conveniently steady bearing load transmission to outside. Finally, transition section, power turbine guider, bearing seat and supply / return oil pipe integration forming, greatly reduced the number of parts, the reduction of the number of parts is very favorable to the improvement assembly, can reduce the weight of engine simultaneously, be favorable to light weight design, in addition, can also reduce the machining cost, improve economy.
[0029] The above only is the preferred implementation of the utility model, should point out, for the ordinary skill in the art of the present technology, on the premise of not departing from the principle of the utility model, still can make a number of improvements, these improvements also should be regarded as the protection scope of the utility model.
Claims
1. A compact transition section, characterized by: The transition section is formed with a transition section support plate (10), the bearing seat (2) is integrally formed with an oil supply / return pipe (1), the right side of the bearing seat (2) is formed with a positioning boss (3), the inner cylindrical surface (30) and the outer cylindrical surface (31) of the positioning boss (3) and the vertical wall surface (20) of the bearing seat (2) respectively form an inner stop structure and an outer stop structure, an elastic support is installed at the inner stop structure to realize the sealing of the bearing seat inner cavity (a) and form an oil cavity of the bearing seat inner cavity, a sealing ring is installed at the outer stop structure to realize the sealing of the transition section inner cavity (b) and form a cold gas cavity of the transition section inner cavity, and the transition section support plate (10) and the guide vane (11) of the power turbine guide are integrally formed together.
2. A compact transition section as claimed in claim 1, characterized in that: The top of the oil supply / return pipe (1) is formed with an external thread part, the transition section support plate (10) is formed with a hollow inner cavity (100) penetrating from top to bottom, and the top of the oil supply / return pipe (1) penetrates through the hollow inner cavity, and the external thread part of the top of the oil supply / return pipe (1) is located above the hollow inner cavity (100).
3. A compact transition section as claimed in claim 2, characterized in that: The bearing seat (2) is formed with a bearing mounting structure (4), and the left side of the bearing mounting structure (4) is mounted with a sealing ring structure (5).
4. A compact transition section as claimed in claim 3, characterized in that: The sealing ring structure (5) is welded with a soft metal structure (7).
5. A compact transition section as claimed in claim 4, characterized in that: The connecting part of the transition section and the bearing seat (2) is designed as a V-shaped structure (6).
6. The compact transition of claim 1, wherein: The transition section support plate (10) and the guide vane (11) are designed as a dot matrix structure (9).
7. A compact transition section as claimed in claim 6, characterized in that: The dot matrix structure is a body-centered cubic structure, an edge structure, a body-centered cubic edge structure or a face-centered cubic edge structure.