CN113236428B

CN113236428B - Turbojet engine

Info

Publication number: CN113236428B
Application number: CN202110774728.XA
Authority: CN
Inventors: 董琨; 谢峤峰; 杨辉; 何家祥
Original assignee: Qinghang Aerospace Beijing Technology Co ltd
Current assignee: Qinghang Aerospace Beijing Technology Co ltd
Priority date: 2021-07-09
Filing date: 2021-07-09
Publication date: 2021-10-01
Anticipated expiration: 2041-07-09
Also published as: CN113236428A

Abstract

A turbojet engine comprising: a bearing housing provided with a first bearing chamber; the fuel distributor comprises a fuel heat exchange seat, at least one part of the fuel heat exchange seat is arranged in the first bearing chamber, a fuel distribution channel is arranged in the fuel heat exchange seat, and an installation cavity is surrounded by the fuel heat exchange seat; a first bearing mounted within the mounting cavity; and a supply member communicating with the fuel distribution passage. Because the fuel in the fuel distribution channel can be used as a heat exchange medium, the fuel heat exchange base can exchange heat with the first bearing equivalently through the heat exchanger, the first bearing is cooled, the working environment of the first bearing is improved, the service life of the first bearing is prolonged, the service life of the turbojet engine is correspondingly prolonged, and the maintenance cost of the turbojet engine is reduced. Meanwhile, the temperature of the fuel is raised after heat exchange, so that the fuel is fully atomized and fully combusted, and the heat efficiency is improved.

Description

Turbojet engine

Technical Field

The present disclosure relates to engine technology, and more particularly, to a turbojet engine.

Background

In the related art, a bearing of the turbojet engine is directly installed in a bearing chamber, a bearing outer ring is connected with the bearing chamber in a matching manner, and an end face of a bearing inner ring is connected with a corresponding rotating part. Along with the increase of the rotating speed of the rotating part, the temperature of the working environment of the bearing is gradually increased, so that the working environment of the bearing is severe, the service life of the bearing is shortened, and the service life of an engine is correspondingly shortened.

Disclosure of Invention

The application provides a turbojet engine can reduce the temperature of bearing to prolong the life of bearing, and then prolong the life of turbojet engine.

In order to achieve the above object, an embodiment of the present application provides a turbojet engine, including: a bearing housing provided with a first bearing chamber; the fuel distributor comprises a fuel heat exchange seat, at least one part of the fuel heat exchange seat is arranged in the first bearing chamber, a fuel distribution channel is arranged in the fuel heat exchange seat, and an installation cavity is surrounded by the fuel heat exchange seat; a first bearing mounted within the mounting cavity; and a supply member communicating with the fuel distribution passage.

The utility model provides a turbojet engine, fuel heat exchange seat has been set up between bearing frame and first bearing, because fuel such as cold fuel oil or normal atmospheric temperature fuel can flow in the fuel distribution passageway of fuel heat exchange seat, fuel can regard as heat transfer medium, thereby make fuel heat exchange seat can be equivalent to the heat exchanger and carry out the heat exchange with first bearing, cool off first bearing, improve the operational environment of first bearing, and then increase the life of first bearing, the corresponding life who improves turbojet engine, and the maintenance cost of turbojet engine has been reduced. Meanwhile, the temperature of the fuel is raised after heat exchange, so that the fuel is fully atomized and fully combusted, and the heat efficiency is improved.

In an exemplary embodiment, further, the fuel heat exchange seat includes: an insertion portion inserted into the first bearing chamber; and the bulge is connected with the inserting part and protrudes out of the first bearing chamber, at least one part of the fuel distribution channel is arranged in the bulge, and at least one part of the mounting chamber is surrounded by the bulge.

In an exemplary embodiment, the bearing seat is provided with a feed opening, the feed opening is connected with the feed member, and the feed opening is communicated with the fuel distribution channel.

In an exemplary embodiment, the fuel distribution channel is disposed within the projection, which encloses a portion of the mounting cavity; and a material passing channel is defined between the bearing seat and the insertion part, and the feed inlet is communicated with the fuel distribution channel through the material passing channel.

In an exemplary embodiment, the number of the feed openings is plural, and the plural feed openings are arranged at intervals along the circumferential direction of the first bearing chamber.

In an exemplary embodiment, the number of the fuel distribution channels is plural, the plural fuel distribution channels are arranged at intervals along the circumferential direction of the projection, and the number of the feed openings is smaller than the number of the fuel distribution channels.

In an exemplary embodiment, the protruding portion abuts against an end surface of the bearing seat, the protruding portion is provided with a first connecting hole through which a fastener passes, the bearing seat is provided with a second connecting hole through which the fastener passes, and the bearing seat, the protruding portion and the guider of the turbojet engine are fixedly connected through the fastener.

In an exemplary embodiment, the number of the first connection holes and the number of the fuel distribution channels are both multiple, and the multiple first connection holes and the multiple fuel distribution channels are arranged in a staggered manner along the circumferential direction of the protrusion.

In an exemplary embodiment, the insertion portion is provided with at least one positioning pin, the bearing seat is provided with a positioning groove corresponding to the position of the positioning pin, and the positioning pin is in concave-convex fit with the positioning groove.

In an exemplary embodiment, the positioning pin is provided on an end face of the insertion portion remote from the projection.

In one illustrative embodiment, the fuel distribution passage includes: a first section in communication with the supply member; and the second section is connected with the first section of the turning part and is communicated with a combustion chamber of the turbojet engine.

In an exemplary embodiment, the cross-sectional area of the second section is less than the cross-sectional area of the first section.

In an exemplary embodiment, the fuel dispenser further comprises: the nozzle is fixedly connected with the fuel distributor, one end of the nozzle is communicated with the fuel distribution channel, and the other end of the nozzle is communicated with a combustion chamber of the turbojet engine.

In an exemplary embodiment, a fuel evaporation tube is provided in the combustion chamber, and a portion of the nozzle is inserted into the fuel evaporation tube.

In an exemplary embodiment, the number of the fuel evaporating pipes is multiple, and the multiple fuel evaporating pipes are arranged at intervals along the circumferential direction of the bearing seat; the number of the nozzles is equal to the number of the fuel evaporating pipes and corresponds to the number of the fuel evaporating pipes one by one.

In an exemplary embodiment, the nozzle and the fuel heat exchange seat are welded to form a one-piece structure.

In an exemplary embodiment, the bearing housing is provided with a second bearing chamber in which a second bearing is mounted; the second bearing is arranged corresponding to a compressor of the turbojet engine, and the first bearing is arranged corresponding to a turbine of the turbojet engine.

Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the application. Other advantages of the present application may be realized and attained by the instrumentalities and combinations particularly pointed out in the specification and the drawings.

Drawings

The accompanying drawings are included to provide an understanding of the present disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the examples serve to explain the principles of the disclosure and not to limit the disclosure.

FIG. 1 is a schematic view of a partial structure of a turbojet engine according to an embodiment of the present application;

FIG. 2 is an enlarged view of portion A of FIG. 1;

FIG. 3 is another schematic partial structure view of a turbojet engine according to an embodiment of the present application;

FIG. 4 is a cross-sectional structural schematic view of a fuel distributor assembly in an embodiment of the present application;

FIG. 5 is a schematic illustration in partial cross-sectional configuration of the fuel distributor assembly of FIG. 4;

wherein the reference numerals in fig. 1 to 5 are as follows:

1, a bearing seat, 11 a first bearing chamber, 111 a feeding hole, 112 a material passing channel, 12 a second bearing chamber and 13 a second connecting hole;

2 fuel distributor, 21 fuel heat exchange seat, 211 insert, 2111 dowel, 212 projection, 213 fuel distribution channel, 2131 first segment, 2132 second segment, 214 mounting cavity, 215 first connection hole, 22 nozzle;

31 a first bearing, 32 a second bearing;

4 a supply member;

5, fastening pieces;

6 combustion chamber, 61 fuel evaporation tube;

71 compressor, 72 turbine, 73 connecting shaft, 74 guider;

wherein the arrows in fig. 2 indicate the flow direction of the fuel.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

As shown in fig. 1, an embodiment of the present invention provides a turbojet engine including: bearing support 1, fuel distributor 2, first bearing 31 and feed block 4.

Specifically, the bearing housing 1 is provided with a first bearing chamber 11, as shown in fig. 1.

The fuel distributor 2 comprises a fuel heat exchange seat 21. At least a portion of the fuel heat exchange seat 21 is installed in the first bearing chamber 11. The fuel heat exchange base 21 is provided with a fuel distribution passage 213 therein, as shown in fig. 2, and the fuel heat exchange base 21 encloses a mounting cavity 214.

The first bearing 31 is mounted in the mounting cavity 214.

The supply member 4 communicates with the fuel distribution passage 213. The feed means 4 may comprise a feed tube.

The turbojet engine provided by the embodiment, fuel heat exchange base 21 is arranged between bearing pedestal 1 and first bearing 31, because fuel such as cold fuel oil or normal temperature fuel oil can flow in fuel distribution channel 213 of fuel heat exchange base 21, fuel can be used as heat exchange medium, thereby enabling fuel heat exchange base 21 to exchange heat with first bearing 31 equivalently, cooling first bearing 31, improving the working environment of first bearing 31, and further increasing the service life of first bearing 31, correspondingly improving the service life of the turbojet engine, and reducing the maintenance cost of the turbojet engine. Meanwhile, the temperature of the fuel is raised after heat exchange, so that the fuel is fully atomized and fully combusted, and the heat efficiency is improved.

Specifically, the turbojet engine includes a bearing seat 1, a fuel distributor 2, a first bearing 31 and a supply component 4, the fuel distributor 2 includes a fuel heat exchange seat 21, and the fuel heat exchange seat 21 is a heat-conducting component and can be made of metal and other materials with good heat-conducting property. At least a part of the fuel heat exchange base 21 is installed in the first bearing chamber 11 of the bearing housing 1, and the first bearing 31 is installed in the installation cavity 214 surrounded by the fuel heat exchange base 21. Thus, when the turbojet engine is operating, the fuel supply member 4 supplies fuel such as cold fuel or normal temperature fuel to the fuel distribution passage 213, and since there is a temperature difference between the fuel and the first bearing 31, the heat of the first bearing 31 is continuously transferred to the fuel in the fuel distribution passage 213 through the fuel heat exchange seat 21, so that the temperature of the fuel increases, and the temperature of the first bearing 31 decreases.

Therefore, the first bearing 31 is cooled, the service life is prolonged, the service life of the turbojet engine is correspondingly prolonged, and the maintenance cost of the turbojet engine is reduced. On the other hand, the fuel obtains the heating and intensifies, is favorable to the abundant atomizing of fuel for the oil-gas mixture is more even, and then the burning is more abundant stable, thereby improves the thermal efficiency of fuel, improves the stability of turbojet engine thrust, improves turbojet engine's economic nature and work efficiency, and the gas that produces after the fuel abundant burning can not cause environmental pollution in discharging into the air, accords with green energy-conserving theory.

In addition, compare in the direct scheme of installing fuel heat exchange seat 21 in bearing frame 1 outside, this scheme installs at least partly fuel heat exchange seat 21 in first bearing room 11, and utilizes fuel heat exchange seat 21 to enclose out the installation cavity 214 that is used for installing first bearing 31, this kind of assembly structure can need not to change the structure of current bearing frame 1, or only need to add slightly to the structure of current bearing frame 1 change can, therefore be convenient for upgrade the improvement on the basis of current product, be favorable to reducing product cost.

It can be understood that the fuel heat exchange base 21 is of an annular structure as a whole, so that the fuel heat exchange base 21 can enclose the installation cavity 214, and after the first bearing 31 is installed in the installation cavity 214, the turbine 72 shaft and other structures of the turbojet engine can pass through the first bearing 31 to be connected with the compressor 71 of the turbojet engine.

In an exemplary embodiment, as shown in fig. 3 and 4, the fuel heat exchange seat 21 includes: an insertion portion 211 and a projection portion 212.

Wherein the insertion portion 211 is inserted into the first bearing chamber 11. The protrusion 212 is connected to the insertion portion 211 and protrudes outside the first bearing chamber 11. At least a portion of fuel distribution channel 213 is disposed within projection 212, and projection 212 encloses at least a portion of mounting cavity 214.

In this embodiment, the fuel heat exchange seat 21 includes an insertion portion 211 and a projection portion 212. The insertion portion 211 is adapted to the structure of the first bearing chamber 11 such that the insertion portion 211 can be inserted into the first bearing chamber 11, which is advantageous for achieving a stable position of the fuel heat exchange housing 21 relative to the bearing housing 1. The protrusion 212 is located outside the first bearing chamber 11, so as to properly arrange the orientation of the fuel distribution channel 213 as required, for example, the fuel can flow into the combustion chamber 6 of the turbojet engine through the fuel distribution channel 213, so as to improve the utilization rate of the fuel. Since at least a portion of the fuel distribution passage 213 is disposed in the protrusion 212 and the protrusion 212 encloses at least a portion of the mounting cavity 214, it is ensured that the first bearing 31 can contact the protrusion 212 and exchange heat with the fuel in the protrusion 212.

In an exemplary embodiment, the housing 1 is provided with a feed opening 111, as shown in fig. 2 and 3. The feed port 111 is connected to the feed member 4, and the feed port 111 communicates with the fuel distribution passage 213.

In the embodiment, since the feeding member 4 is closer to the bearing housing 1 and the bearing housing 1 is closer to the fuel distribution channel 213 in the related art, the bearing housing 1 is provided with the feeding hole 111 communicating with the fuel distribution channel 213, so that the feeding hole 111 is connected to the feeding member 4, and the feeding member 4 and the fuel distribution channel 213 can be indirectly communicated with each other through the feeding hole 111. Compared with the scheme that the feeding component 4 is directly connected with the fuel heat exchange seat 21, the scheme is favorable for shortening the length of the feeding component 4, optimizing the pipeline layout of the turbojet engine and simplifying the structure of the fuel heat exchange seat 21.

In an exemplary embodiment, fuel distribution channel 213 is disposed within protrusion 212, and protrusion 212 encloses a portion of mounting cavity 214. The bearing seat 1 and the insertion part 211 define a material passing channel 112 therebetween, as shown in fig. 2. The feed port 111 communicates with the fuel distribution channel 213 through the flash passage 112.

Providing the fuel distribution channel 213 entirely within the projection 212 is advantageous to simplify the structure of the fuel distribution channel 213. The protrusion 212 encloses a portion of the mounting cavity 214, and the insertion portion 211 also encloses a portion of the mounting cavity 214, so that a portion of the first bearing 31 remains inside the bearing housing 1. Compared with the scheme that the first bearing 31 is completely positioned outside the bearing seat 1, the scheme is favorable for shortening the axial size of the turbojet engine, and therefore the size of the turbojet engine is favorably reduced.

Further, a material passing channel 112 is defined between the inner wall surface of the bearing seat 1 and the insertion part 211, one end of the material passing channel 112 is communicated with the feed port 111, and the other end of the material passing channel 112 is communicated with the fuel distribution channel 213, so that the feed port 111 is communicated with the fuel distribution channel 213. In this way, the fuel in the material passing channel 112 can also absorb the heat of the first bearing 31, so that the cooling effect on the first bearing 31 is improved, and the heating efficiency on the fuel is also improved.

On the other hand, the feed inlet 111 is indirectly communicated with the fuel distribution channel 213 through the material passing channel 112, and the shape of the material passing channel 112 can be reasonably arranged as required, so that the feed inlet 111 and the fuel distribution channel 213 do not need to correspond one to one, and thus, a small number of feed inlets 111 can be used for conveying fuel for a large number of fuel distribution channels 213, the number of the feed parts 4 is reduced, the pipeline layout of the turbojet engine is simplified, the uniformity of the fuel is improved by using a large number of fuel distribution channels 213, carbon deposition caused by insufficient fuel combustion is prevented, and the economy and the working efficiency of the turbojet engine are improved.

For example, the material passing channel 112 is annular, that is: a ring of channels surrounding the insertion portion 211 is formed between the inner circumferential wall of the bearing housing 1 and the outer circumferential wall of the insertion portion 211. Thus, a material passing channel 112 can be communicated with one or more feed openings 111 and also communicated with one or more fuel distribution channels 213.

Alternatively, the cross section of the material passing channel 112 may not be a complete circle, but may be an arc-shaped structure, and the communication between the feed port 111 and the fuel distribution channel 213 may also be realized by providing a plurality of material passing channels 112.

In an exemplary embodiment, the number of the feed ports 111 is plural, and the plural feed ports 111 are provided at intervals in the circumferential direction of the first bearing chamber 11.

The number of the feed openings 111 is plural, and the number of the feed member 4 is plural accordingly. Thus, the fuel supply efficiency is improved, the pressure of the fuel sprayed out from each fuel distribution channel 213 is more uniform, the atomization effect of the fuel is further improved, and the carbon deposition caused by insufficient combustion is avoided, so that the working efficiency of the turbojet engine is further improved.

Further, the plurality of feed ports 111 are uniformly arranged in the circumferential direction of the first bearing chamber 11.

In an exemplary embodiment, the number of the fuel distribution passage 213 is plural, and as shown in fig. 5, the plural fuel distribution passages 213 are provided at intervals in the circumferential direction of the projection 212. Like this, the fuel of fuel distributor 2 output is more even, is favorable to improving atomization effect, is favorable to the intensive mixing of oil gas, and then is favorable to realizing complete combustion. The number of the feed openings 111 is smaller than the number of the fuel distribution passages 213, which is advantageous in reducing the number of the feed member 4 to simplify the piping layout of the turbojet engine.

Further, a plurality of fuel distribution channels 213 are uniformly arranged in the circumferential direction of the projection 212, as shown in fig. 5.

In an exemplary embodiment, as shown in fig. 3, the protruding portion 212 abuts against an end surface of the bearing housing 1, the protruding portion 212 is provided with a first connection hole 215 for the fastener 5 to pass through, the bearing housing 1 is provided with a second connection hole 13 for the fastener 5 to pass through, and the bearing housing 1, the protruding portion 212 and the guide 74 of the turbojet engine are fixedly connected by the fastener 5.

This scheme utilization fastener 5 has realized the fixed connection of bearing frame 1, fuel heat exchange seat 21, first bearing 31, and is fixed firm, and intensity is high. Wherein the fastener 5 may be a bolt.

Further, the number of the fastening members 5 is plural, and the plural fastening members 5 are provided at intervals in the circumferential direction of the bearing housing 1. Further, the plurality of fastening members 5 are uniformly arranged along the circumferential direction of the bearing housing 1, which facilitates the force balance among the bearing housing 1, the fuel heat exchange housing 21, and the guide 74.

In an exemplary embodiment, the first connection hole 215 and the fuel distribution channel 213 are each plural in number. In this way, the number of the fastening members 5 is also plural, and the plural fastening members 5 are provided at intervals in the circumferential direction of the bearing housing 1. The bearing seat 1, the fuel heat exchange seat 21 and the guider 74 are fixedly connected through a plurality of fasteners 5, the strength is higher, and the fixation is more reliable.

Further, the plurality of fastening members 5 are uniformly arranged along the circumferential direction of the bearing housing 1, which facilitates the force balance among the bearing housing 1, the fuel heat exchange housing 21, and the guide 74.

Further, as shown in fig. 5, the plurality of first connection holes 215 and the plurality of fuel distribution passages 213 are arranged offset in the circumferential direction of the projection 212. This is advantageous for improving the strength of the fuel heat exchange base 21, and preventing the local strength from being too low due to too dense local holes of the fuel heat exchange base 21, thereby improving the reliability of the fuel heat exchange base 21.

In an exemplary embodiment, as shown in fig. 5, the insertion portion 211 is provided with at least one positioning pin 2111, and the bearing seat 1 is provided with a positioning groove (not shown) corresponding to the position of the positioning pin 2111, and the positioning pin 2111 is in concave-convex fit with the positioning groove.

The insertion part 211 and the bearing seat 1 can be assembled and pre-fixed through the matching of the positioning pin 2111 and the positioning groove, so that the hole positions of the bearing seat 1 and the fuel heat exchange seat 21 are aligned, and the subsequent fixed connection can be realized through the fastening pieces 5 such as bolts. Therefore, the matching of the positioning pin 2111 and the positioning groove reduces the assembly difficulty of the turbojet engine and improves the assembly efficiency.

In an exemplary embodiment, the locating pin 2111 is provided on an end surface of the insertion portion 211 remote from the projection 212. In this way, the fuel heat exchange seat 21 is directly inserted into the bearing seat 1 along the axial direction of the bearing seat 1, and the insertion process is not easy to interfere, so that the assembly difficulty is reduced, and the assembly efficiency is improved.

In one exemplary embodiment, as shown in fig. 4 and 5, the fuel distribution passage 213 includes: a first segment 2131 and a second segment 2132.

Wherein the first section 2131 is in communication with the feed means 4. The second section 2132 is connected to the first section 2131, and the second section 2132 is in communication with the combustion chamber 6 of the turbojet engine.

In this way, the fuel delivered by the feeding component 4 enters the combustion chamber 6 for combustion after heat exchange with the first bearing 31 through the fuel heat exchange seat 21, so that the first bearing 31 is cooled and the fuel is preheated before combustion. Therefore, the fuel heat exchange seat 21 not only has the function of a fuel heat exchanger, but also has the functions of distributing fuel and preheating and heating the fuel, integrates a plurality of functions, and is ingenious in conception.

On the other hand, the fuel distribution passage 213 includes a first section 2131 and a second section 2132 connected in a zigzag manner, which facilitates the rational arrangement of the feed block 4 as required to optimize the piping layout of the turbojet engine.

Further, the first segment 2131 extends in the axial direction of the first bearing 31, and the second segment 2132 extends in the radial direction of the first bearing 31. The second section 2132 is vertically connected to the first section 2131.

In an exemplary embodiment, the cross-sectional area of the second section 2132 is less than the cross-sectional area of the first section 2131.

The cross-sectional area of the first section 2131 is relatively large to facilitate rapid entry of fuel provided by the feed block 4 into the fuel distribution passage 213. The cross-sectional area of the second section 2132 is relatively small, which is beneficial to improving the flow velocity of the fuel output by the fuel conveying channel and is convenient for full atomization after the fuel is sprayed out.

In one illustrative embodiment, the fuel dispenser 2 further comprises: the nozzle 22 is shown in fig. 2, 4 and 5. The nozzle 22 is fixedly connected to the fuel distributor 2, one end of the nozzle 22 communicates with the fuel distribution passage 213, and the other end of the nozzle 22 communicates with the combustion chamber 6 of the turbojet engine.

Further, a fuel evaporation pipe 61 is provided in the combustion chamber 6, as shown in fig. 1. A part of the nozzle 22 is inserted into the fuel evaporation tube 61 as shown in fig. 2.

The nozzle 22 increases the flow rate of the fuel delivered by the fuel dispenser 2 to facilitate efficient atomization of the fuel and thus efficient combustion of the fuel.

The fuel evaporation tube 61 can evaporate the liquid fuel, and is more beneficial to the full atomization of the fuel by cooperating with the nozzle 22, thereby being beneficial to the full combustion of the fuel.

In an exemplary embodiment, the number of the fuel-evaporating tubes 61 is plural, and the plural fuel-evaporating tubes 61 are arranged at intervals in the circumferential direction of the bearing housing 1. The number of the nozzles 22 is equal to and corresponds one-to-one to the number of the fuel evaporating tubes 61.

This is beneficial to improving the fuel uniformity of each part in the combustion chamber 6, and further improving the thrust stability of the turbojet engine.

Further, the plurality of fuel evaporating pipes 61 are uniformly arranged along the circumferential direction of the bearing housing 1, which is advantageous for further improving the uniformity of fuel distribution. The nozzle 22 is in the shape of a bent tube, as shown in fig. 2.

In an exemplary embodiment, the nozzle 22 and the fuel heat exchanger seat 21 are welded together as a single piece.

The nozzle 22 and the fuel heat exchange seat 21 are integrally formed by adopting a welding process, so that the connection strength is high, the fixation is reliable, the sealing of the connection part is realized, and the leakage of the fuel at the connection part of the nozzle 22 and the fuel heat exchange seat 21 is favorably prevented.

In an exemplary embodiment, as shown in FIG. 1, the bearing housing 1 is provided with a second bearing chamber 12, the second bearing chamber 12 having a second bearing 32 mounted therein. The second bearing 32 is provided corresponding to a compressor 71 of the turbojet engine, and the first bearing 31 is provided corresponding to a turbine 72 of the turbojet engine.

The turbojet engine comprises a compressor 71 and a turbine 72, wherein the compressor 71 and the turbine 72 are coaxially connected, and a connecting shaft 73 is supported by a first bearing 31 and a second bearing 32. As the rotating speed of the turbine 72 increases, the temperature of the turbine 72 and the temperature of the guider 74 also increase correspondingly, the temperature in front of the turbine 72 can reach 1000 ℃ at most, and the corresponding radiation temperature for the first bearing 31 can reach 400-500 ℃, so that the working environment of the first bearing 31 is quite severe, the service life of the first bearing 31 is shortened, and the service life of the turbojet engine is also shortened correspondingly.

The operating temperature of the second bearing 32 is relatively low, around 80 ℃. Therefore, the service life of the turbojet engine can be prolonged by only utilizing the fuel distributor 2 to cool the first bearing 31.

In one exemplary embodiment, the turbojet engine is a small turbojet engine.

One embodiment is described below with reference to the drawings.

As shown in fig. 1, the present embodiment provides a small turbojet engine including: the structure comprises a bearing seat 1, a fuel distributor 2, a first bearing 31, a second bearing 32, a feeding component 4, a combustion chamber 6, a guider 74, a fuel evaporation pipe 61, a compressor 71, a turbine 72 and the like.

The fuel distributor 2 comprises a fuel heat exchange seat 21 and eight nozzles 22, as shown in fig. 5. The fuel heat exchange holder 21 includes an insertion portion 211 and a projection portion 212, as shown in fig. 4. The end face of the insertion portion 211 remote from the projection 212 is provided with two positioning pins 2111, as shown in fig. 5. Eight fuel distribution passages 213 are uniformly provided in the projection 212 in the circumferential direction, as shown in fig. 5. The fuel distribution channel 213 includes a first section 2131 and a second section 2132, as shown in fig. 4 and 5. The nozzle 22 has one end connected to the second segment 2132 and the other end inserted into the fuel evaporation tube 61, as shown in fig. 2. The fuel-evaporating tube 61 is located inside the combustion chamber 6, as shown in fig. 1.

The bearing housing 1 is provided at both ends thereof with a first bearing chamber 11 and a second bearing chamber 12, respectively, as shown in fig. 1. The first bearing chamber 11 is provided with two positioning recesses (not shown in the figure). The insertion portion 211 of the fuel heat exchange holder 21 is inserted into the first bearing chamber 11, as shown in fig. 1. And the insertion portion 211 is pre-positioned in the first bearing chamber 11 by the two positioning pins 2111 matching with the two positioning grooves. The first bearing 31 is mounted in the mounting cavity 214. The bearing housing 1, the projection 212 and the guide 74 are fixedly connected by eight bolts.

The feed member 4 comprises two feed pipes, as shown in fig. 1. The bearing seat 1 is provided with two feed inlets 111, and the two feed inlets 111 are correspondingly connected with two feed pipes. The bearing seat 1 and the insertion part 211 form a material passing channel 112 therebetween as shown in fig. 2. The two feed ports 111 communicate with the eight fuel distribution passages 213 through the flash passage 112.

The second bearing 32 is mounted within the second bearing chamber 12 as shown in FIG. 1. The compressor 71 and the turbine 72 are coaxially connected by a connecting shaft 73. The connecting shaft 73 has both ends connected to the first bearing 31 and the second bearing 32, respectively, and is supported by the first bearing 31 and the second bearing 32. In other words, the connecting shaft 73 is supported at two points, the front point being behind the compressor 71 and the rear point being in front of the guide 74 and the turbine 72. The connecting shaft 73 may be a hollow shaft or a solid shaft; the connecting shaft 73 may be one member or an assembly formed by connecting a plurality of members.

This small-size turbojet engine adopts above-mentioned scheme, has following beneficial effect: 1) by adopting the fuel distributor, the fuel supply is changed from one original fuel supply to two fuel supplies, so that the pressure of the fuel sprayed by each nozzle is more uniform, the temperature of the fuel is improved, the atomization effect is better, the oil-gas mixing is more uniform, the insufficient combustion is avoided, and the carbon deposition phenomenon is avoided; 2) the combustion is stable, so that the thrust stability of the small turbojet engine is ensured; 3) the fuel is fully and completely combusted, so that the economy and the efficiency of the turbojet engine are ensured, and the completely combusted fuel gas is discharged into the air without causing environmental pollution; 4) the fuel distributor is adopted to replace the part of the first bearing chamber connected with the first bearing, the service environment of the bearing (namely the first bearing) in the high-temperature area is improved, the working temperature of the bearing in the high-temperature area is reduced from about 500 ℃ to about 300 ℃, the service life of the bearing in the high-temperature area is prolonged, the service life of the small-sized turbojet engine is prolonged, the maintenance cost is reduced, and the economy of the small-sized turbojet engine is improved.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims

1. A turbojet engine, comprising:

a bearing housing provided with a first bearing chamber;

the fuel distributor comprises a fuel heat exchange seat, at least one part of the fuel heat exchange seat is arranged in the first bearing chamber, a fuel distribution channel is arranged in the fuel heat exchange seat, and an installation cavity is surrounded by the fuel heat exchange seat;

a first bearing mounted within the mounting cavity; and

a feed member in communication with the fuel distribution passage;

the fuel heat exchange seat includes:

an insertion portion inserted into the first bearing chamber; and

the protruding part is connected with the inserting part and protrudes out of the first bearing chamber, at least one part of the fuel distribution channel is arranged in the protruding part, and at least one part of the mounting chamber is surrounded by the protruding part.

2. The turbojet engine of claim 1,

the bearing frame is equipped with the feed inlet, the feed inlet with the feeding part links to each other, just the feed inlet with fuel distribution channel intercommunication.

3. The turbojet engine of claim 2,

the fuel distribution channel is arranged in the bulge part, and the bulge part surrounds a part of the mounting cavity;

and a material passing channel is defined between the bearing seat and the insertion part, and the feed inlet is communicated with the fuel distribution channel through the material passing channel.

4. The turbojet engine of claim 2,

the quantity of feed inlet is a plurality of, and is a plurality of the feed inlet is followed the circumference interval setting of first bearing chamber.

5. The turbojet engine of claim 4,

the number of fuel distribution passageway is a plurality of, and is a plurality of fuel distribution passageway sets up along the circumference interval of bulge, just the quantity of feed inlet is less than the number of fuel distribution passageway.

6. The turbojet engine of any one of claims 1 to 5,

the bulge butt in the terminal surface of bearing frame, the bulge is equipped with the first connecting hole that supplies the fastener to pass, the bearing frame is equipped with the second connecting hole that supplies the fastener to pass, the bearing frame, the bulge and turbojet engine's director passes through fastener fixed connection.

7. The turbojet engine of claim 6,

the first connecting hole with the quantity of fuel distribution passageway is a plurality of, and is a plurality of first connecting hole is with a plurality of fuel distribution passageway is followed the setting of staggering of circumference of bulge.

8. The turbojet engine of any one of claims 1 to 5,

the inserting portion is provided with at least one positioning pin, a positioning groove is formed in the position, corresponding to the positioning pin, of the bearing seat, and the positioning pin is in concave-convex fit with the positioning groove.

9. The turbojet engine of claim 8,

the positioning pin is arranged on the end face of the insertion part far away from the protruding part.

10. The turbojet engine of any one of claims 1 to 5, wherein the fuel distribution channel comprises:

a first section in communication with the supply member; and

and the second section is connected with the first section of the turning part and is communicated with a combustion chamber of the turbojet engine.

11. The turbojet engine of claim 10,

the cross-sectional area of the second section is less than the cross-sectional area of the first section.

12. The turbojet engine of any one of claims 1 to 5, wherein the fuel distributor further comprises:

the nozzle is fixedly connected with the fuel distributor, one end of the nozzle is communicated with the fuel distribution channel, and the other end of the nozzle is communicated with a combustion chamber of the turbojet engine.

13. The turbojet engine of claim 12,

a fuel evaporation pipe is arranged in the combustion chamber, and a part of the nozzle is inserted into the fuel evaporation pipe.

14. The turbojet engine of claim 13,

the number of the fuel evaporating pipes is multiple, and the multiple fuel evaporating pipes are arranged at intervals along the circumferential direction of the bearing seat;

the number of the nozzles is equal to the number of the fuel evaporating pipes and corresponds to the number of the fuel evaporating pipes one by one.

15. The turbojet engine of claim 12,

the nozzle and the fuel heat exchange seat are of an integrated structure formed by welding.

16. The turbojet engine of any one of claims 1 to 5,

the bearing seat is provided with a second bearing chamber, and a second bearing is arranged in the second bearing chamber;

the second bearing is arranged corresponding to a compressor of the turbojet engine, and the first bearing is arranged corresponding to a turbine of the turbojet engine.