Engine

Abstract

The invention relates to the technical field of power equipment, and discloses an engine which comprises a rotating shaft, a first gas compressor, a second gas compressor and a sealing unit, the sealing unit is arranged, the contact area between second gas flow and first end teeth can be reduced through the sealing unit, and the influence of the second gas flow on the temperature of the first end teeth is reduced; and meanwhile, the first through hole is formed, the first air flow can be guided to the position of the first end tooth through the first through hole, the first end tooth is cooled, it is ensured that the first end tooth can bear the temperature in the engine after being made of the light alloy, and therefore the technical effect of prolonging the service life of the first end tooth is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of power equipment, in particular to an engine. Background Art

[0002] In the field of aviation technology, the engine is an indispensable power device, and the compressor is an important part of the engine. The impeller on the compressor drives the fluid to move and compress the fluid. The compressed fluid enters the combustion chamber, mixes with the fuel in the combustion chamber and burns to produce high-temperature and high-pressure gas, which is finally ejected through the nozzle connected to the combustion chamber as the power for the engine to work. Among them, the end face of the impeller is provided with end teeth to connect other components through the end teeth. The stability of the impeller transmission can be improved by setting the end teeth.

[0003] The existing engine includes a two-stage compressor, a rotating shaft and an isolation structure. The two-stage compressors are an axial flow compressor and a centrifugal compressor respectively. The axial flow compressor and the centrifugal compressor are both spaced apart and sleeved on the rotating shaft. The airflow of the engine enters from the air inlet of the axial flow compressor, and is divided into two flow paths after being compressed by the axial flow compressor, namely the first airflow and the first main flow path.

[0004] The first airflow flows downstream (away from the axial compressor) away from the axial compressor and along the axis parallel to the rotating shaft. The first main flow path passes through the centrifugal compressor, wherein the centrifugal compressor includes a first air outlet and a second air outlet, wherein the first air outlet is arranged through the root of the impeller of the centrifugal compressor, and the second air outlet is arranged toward the combustion chamber. The gas of the first main flow path forms a second main flow path through the second air outlet and enters the combustion chamber. The gas of the first main flow path forms a second airflow through the first air outlet. The second airflow passes through the air outlet of the centrifugal compressor and flows along the surface of the centrifugal compressor, passes through the first end tooth, and then flows downstream along the axis of the rotating shaft. Since the second airflow passes through the interior of the centrifugal compressor, the temperature of the second airflow is higher than that of the first airflow.

[0005] The isolation structure is used to isolate the first airflow and the second airflow. When the first airflow and the second airflow flow downstream, the first airflow and the second airflow flow along the two sides of the isolation structure to prevent the mixing of the first airflow and the second airflow from affecting the cooling effect of the downstream engine structure. Specifically, the isolation structure rotates synchronously with the centrifugal compressor, the end of the centrifugal compressor is provided with a first end tooth, and the end of the isolation structure is provided with a second end tooth. The first end tooth and the second end tooth are meshed to realize the centrifugal compressor driving the rotation of the isolation structure.

[0006] During this process, the second airflow flows to one side of the isolation structure through the gap between the first end teeth and the second end teeth, and the temperature of the second airflow causes the temperature of the first end teeth and the second end teeth to rise. As the existing engines have increasingly higher requirements for cycle parameters and thrust-to-weight ratio, the impeller, the first end teeth and the second end teeth need to be made of light alloys, resulting in the first end teeth and the second end teeth having weak heat resistance and being unable to withstand the temperature of the second airflow, causing the first end teeth and the second end teeth to fail, affecting the normal use of the engine. Summary of the invention

[0007] In view of this, the present invention provides an engine to solve the problem in existing engines that the impeller, the first end teeth and the second end teeth are made of light alloy, causing the impeller end teeth to fail due to being unable to withstand the heat inside the engine, thus affecting the normal use of the engine.

[0008] The present invention provides an engine, comprising:

[0009] Rotating shaft;

[0010] a first compressor, rotatably connected to the rotating shaft, wherein an air inlet is provided at one end of the first compressor, and a first air outlet and a second air outlet are provided at the other end of the first compressor, and air flowing out of the first air outlet forms a first airflow;

[0011] A second compressor is rotatably connected to the rotating shaft and is arranged on one side of the first compressor, the second compressor comprises a connected main body and a blade root, one end of the main body is communicated with the second air outlet, and the other end of the main body is provided with a third air outlet communicated with the second air outlet, the air flowing out of the third air outlet forms a second airflow, and the temperature of the second airflow is higher than that of the first airflow; a first side of the blade root is located on the flow path of the first airflow, and a second side of the blade root is located on the flow path of the second airflow, an end of the blade root away from the first compressor is provided with a first end tooth, and a first through hole is opened on the first side of the blade root in the direction of the first end tooth, and the first through hole is used to adjust the first airflow to flow through the first end tooth;

[0012] A sealing unit is provided on the inner diameter of the first end tooth and / or the outer diameter of the first end tooth, and is used to isolate the first airflow and the second airflow on both sides of the first end tooth.

[0013] Beneficial effects: By setting up a sealing unit, the sealing unit can reduce the contact area between the second airflow and the first end tooth, thereby reducing the influence of the second airflow on the temperature of the first end tooth. At the same time, by setting up a first through hole, the first through hole can guide the first airflow to the position of the first end tooth to cool the first end tooth, thereby ensuring that the first end tooth can withstand the temperature inside the engine after using a light alloy, thereby achieving the technical effect of increasing the service life of the first end tooth.

[0014] In an optional embodiment, the sealing unit is arranged on the inner diameter of the first end tooth, and the material of the sealing unit is a heat-conducting material.

[0015] Beneficial effect: The sealing unit is arranged at the inner diameter of the first end tooth, which can not only form a barrier to the first airflow and the second airflow, but also prevent the second airflow from flowing through the gap of the first end tooth, thereby achieving the technical effect of reducing the contact area between the second airflow and the first end tooth and reducing the influence of the temperature of the second airflow on the temperature of the first end tooth. At the same time, the material of the sealing unit is a heat-conducting material, so that the temperature of the first airflow can be transferred to the first end tooth through the sealing unit, that is, the first airflow cools the sealing unit to achieve the cooling of the first end tooth, thereby improving the cooling capacity of the first end tooth.

[0016] In an optional embodiment, a plurality of heat-conducting parts are provided on a side of the sealing unit away from the first end tooth, and the heat-conducting parts are protruding in a direction away from the first end tooth.

[0017] Beneficial effect: The protruding setting of the heat-conducting part can increase the contact area between the first airflow and the sealing unit, so that the first airflow can better cool the sealing unit to enhance the cooling effect on the first end tooth.

[0018] In an optional embodiment, the plurality of heat conducting parts are arranged in multiple rows and columns;

[0019] And / or, heat conducting holes are provided on the side surface of the heat conducting portion and / or the end surface of the heat conducting portion away from the sealing unit.

[0020] Beneficial effect: By arranging the multiple heat-conducting parts in multiple rows and columns, the connection points between the heat-conducting parts and the seal can be increased, thereby improving the cooling effect on the first end teeth.

[0021] And / or, the contact area between the first airflow and the sealing unit can be further increased through the heat conduction hole, thereby achieving the technical effect of improving the sealing unit's ability to cool the first end teeth.

[0022] In an optional embodiment, a cavity is provided on one side of the blade root, and the cavity is arranged close to the first end tooth.

[0023] Beneficial effects: The cavity is provided to reduce the weight of the blade root, reduce the inertia force borne by the blade root, and improve the dynamic response and reliability of the blade root.

[0024] In an optional embodiment, a second through hole is provided on the first side of the blade root facing the cavity, and the second through hole is communicated with the cavity.

[0025] Beneficial effect: By passing the first airflow through the second through hole to cool the inside of the cavity, the temperature of the second compressor inside the cavity is prevented from affecting the cooling effect of the first end tooth, thereby achieving the technical effect of improving the cooling capacity of the first end tooth.

[0026] In an optional embodiment, a central axis of the first through hole forms an angle with a straight line passing through the first through hole and perpendicular to the rotation axis.

[0027] Beneficial effect: By limiting the relationship between the first through hole and the straight line perpendicular to the rotating shaft, the velocity of the first airflow can be divided into a component velocity along the axial direction and a component velocity along the circumferential direction, so as to increase the movement time of the first airflow along the circumferential direction, thereby enhancing the cooling effect of the first airflow on the surrounding structure of the first end tooth, reducing the heat energy transferred to the first end tooth by the surrounding structure of the first end tooth, and thereby achieving the technical effect of improving the cooling efficiency of the first end tooth.

[0028] In an optional embodiment, the engine comprises:

[0029] The barrier unit comprises a second end tooth, wherein the second end tooth is meshingly connected with the first end tooth, and along the axial direction of the rotating shaft, the sealing unit at least covers the meshing ends of the second end tooth and the first end tooth.

[0030] Beneficial effect: The meshing position between the second end tooth and the first end tooth can be sealed by a sealing unit to prevent the second airflow from flowing to the first airflow through the meshing gap, increasing the temperature of the first airflow and affecting the cooling effect of the first airflow on the internal structure of the engine.

[0031] In an optional embodiment, the barrier unit includes:

[0032] A first blocking portion is sleeved on the rotating shaft at intervals, one end of the first blocking portion is provided with the second end tooth, and the other end of the first blocking portion extends in a direction away from the second end tooth;

[0033] A second blocking part is sleeved on the rotating shaft at intervals, the second blocking part is arranged close to the rotating shaft, one end of the second blocking part is fixedly connected to the first blocking part, a gap between the second blocking part and the rotating shaft is communicated with the cavity, and the other end of the second blocking part extends in a direction away from the first end tooth;

[0034] The first airflow flows along a side of the second blocking portion close to the rotating shaft, and the second airflow flows along a side of the first blocking portion away from the rotating shaft.

[0035] Beneficial effect: Through the setting of the first blocking part and the second blocking part, the first airflow and the second airflow can be blocked to avoid mixing of the first airflow and the second airflow during flow, thereby affecting the temperature of the first airflow and further affecting the cooling effect of the first airflow on the first end tooth and the second end tooth, thereby achieving the technical effect of improving the cooling capacity of the first end tooth and the second end tooth.

[0036] In an optional embodiment, a third through hole is provided at one end of the first blocking portion away from the second end tooth, and the third through hole is used to guide the second airflow to a side of the second blocking portion away from the rotating shaft.

[0037] Beneficial effect: The second airflow can be guided toward the direction close to the rotating shaft through the third through hole. Based on this, the flow paths of the first airflow and the second airflow away from the second compressor are not adjusted, that is, the first airflow and the second airflow still flow along the original flow path in the relevant technology, so as to achieve the technical effect of ensuring that the degree of adjustment to the engine structure is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0039] Figure 1 is a partial schematic diagram of an engine of this embodiment;

[0040] Figure 2 is a partial schematic diagram of the sealing unit in this embodiment;

[0041] Figure 3 is a front view of the sealing unit in this embodiment;

[0042] Figure 4 2 is a cross-sectional view of the sealing unit in this embodiment.

[0043] Description of reference numerals:

[0044] 1. first compressor; 101. first air outlet; 102. first air flow;

[0045] 2. Second compressor; 201. Main body;

[0046] 202, blade root; 2021, cavity; 2022, first end tooth; 2023, second through hole;

[0047] 203, third air outlet; 204, second air flow; 205, first through hole;

[0048] 3. Sealing unit;

[0049] 4. barrier unit; 401. first barrier portion; 4011. second end tooth; 4012. third through hole;

[0050] 402, second barrier portion;

[0051] 5. heat conducting part; 501. first hole; 502. second hole;

[0052] 6. Center pull rod. DETAILED DESCRIPTION

[0053] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0054] Combine the following Figures 1 to 4 , describing an embodiment of the present invention.

[0055] According to an embodiment of the present invention, there is provided an engine, comprising:

[0056] Rotating shaft;

[0057] A first compressor 1 is rotatably connected to the rotating shaft, an air inlet is provided at one end of the first compressor 1, and a first air outlet 101 and a second air outlet are provided at the other end of the first compressor 1, and air flowing out of the first air outlet 101 forms a first airflow 102;

[0058] The second compressor 2 is rotatably connected to the rotating shaft and is arranged on one side of the first compressor 1. The second compressor 2 includes a connected main body 201 and a blade root 202. One end of the main body 201 is connected to the second air outlet. The other end of the main body 201 is provided with a third air outlet 203 connected to the second air outlet. The air flowing out of the third air outlet 203 forms a second air flow 204. The temperature of the second air flow 204 is higher than that of the first air flow 102. The first side of the blade root 202 is located on the flow path of the first air flow 102. The second side of the blade root 202 is located on the flow path of the second air flow 204. The end of the blade root 202 away from the first compressor 1 is provided with a first end tooth 2022. The first side of the blade root 202 is provided with a first through hole 205 in the direction of the first end tooth 2022. The first through hole 205 is used to adjust the first air flow 102 to flow through the first end tooth 2022.

[0059] The sealing unit 3 is disposed on the inner diameter of the first end tooth 2022 and / or the outer diameter of the first end tooth 2022 , and is used to isolate the first airflow 102 and the second airflow 204 on both sides of the first end tooth 2022 .

[0060] In the engine of this embodiment, by setting the sealing unit 3, the sealing unit 3 can reduce the contact area between the second airflow 204 and the first end tooth 2022, thereby reducing the influence of the second airflow 204 on the temperature of the first end tooth 2022. At the same time, by setting the first through hole 205, the first through hole can guide the first airflow 102 to the position of the first end tooth 2022, thereby cooling the first end tooth 2022 and ensuring that the first end tooth 2022 can withstand the temperature inside the engine after using light alloy, thereby achieving the technical effect of increasing the service life of the first end tooth 2022.

[0061] In this embodiment, the inner diameter is the side of the first end tooth 2022 close to the shaft, and the outer diameter is the side of the first end tooth 2022 away from the shaft. The shaft is not shown in the figure. The axis of the shaft is along Figure 1 Horizontal settings shown.

[0062] In addition, in this embodiment, the first compressor 1 is an axial compressor, and the second compressor 2 is a centrifugal compressor. The axial compressor and the centrifugal compressor are provided with a central tie rod 6 on one side close to the rotating shaft. The central tie rod 6 is an essential part of the engine and will not be described in detail here. The centrifugal compressor and the central tie rod 6 are arranged at intervals, and the first airflow 102 is arranged along the gap between the centrifugal compressor and the central tie rod 6. Figure 1 Flow to the right as shown.

[0063] Of course, in other embodiments, the type of the first compressor 1 and the type of the second compressor 2 may be adjusted according to different types of engines.

[0064] In addition, in this embodiment, the sealing unit 3 is arranged on the inner diameter of the first end tooth 2022, that is, the sealing unit 3 is an annular structure. The sealing unit 3 can not only form a barrier to the first airflow 102 and the second airflow 204, but also prevent the second airflow 204 from flowing through the gap of the first end tooth 2022, thereby achieving the technical effect of reducing the contact area between the second airflow 204 and the first end tooth 2022 and reducing the influence of the high temperature of the second airflow 204 on the temperature of the first end tooth 2022.

[0065] Meanwhile, the sealing unit 3 is made of a heat-conducting material, for example, the sealing unit 3 may be made of stainless steel, so that the temperature of the first airflow 102 can be transferred to the first end tooth 2022 through the sealing unit 3, that is, the first airflow 102 cools the sealing unit 3 to cool the first end tooth 2022, thereby improving the cooling capacity of the first end tooth 2022. As a convertible embodiment, the sealing unit 3 may also be made of copper or other materials with heat conductivity.

[0066] Of course, in other embodiments, the sealing unit 3 can be arranged on the outer diameter of the first end tooth 2022, so that the first end tooth 2022 can be completely blocked from the second airflow 204. At this time, a thermal insulation coating can be coated on the surface of the sealing unit 3 away from the first end tooth 2022, or the material of the sealing unit 3 can be directly a thermal insulation material, so that the first end tooth 2022 cannot contact the second airflow 204, thereby improving the thermal conductivity effect of the sealing unit 3 on the first end tooth 2022.

[0067] In addition, in this embodiment, combined with Figures 2 to 4 As shown, a plurality of heat-conducting parts 5 are provided on a side of the sealing unit 3 away from the first end teeth 2022 , and the heat-conducting parts 5 are protruded in a direction away from the first end teeth 2022 .

[0068] The protruding arrangement of the heat conducting portion 5 can increase the contact area between the first airflow 102 and the sealing unit 3 , so that the first airflow 102 can better cool the sealing unit 3 , thereby improving the cooling effect on the first end teeth 2022 .

[0069] Specifically, the plurality of heat conducting parts 5 are crisscrossed to form a mesh structure to increase the connection points between the heat conducting parts 5 and the seal, thereby improving the cooling effect on the first end teeth 2022 .

[0070] Of course, in other embodiments, the shape of the heat conducting portion 5 may be adaptively adjusted according to different engine designs.

[0071] In other embodiments, the heat conducting part 5 may not be provided, and the first airflow 102 only conducts heat to the first end teeth 2022 through the sealing unit 3 .

[0072] In addition, in this embodiment, combined with Figures 2 to 4 As shown, heat conducting holes are provided on the side surface of the heat conducting portion 5 and the end surface of the heat conducting portion 5 away from the sealing unit 3 .

[0073] The contact area between the first airflow 102 and the sealing unit 3 can be further increased through the heat-conducting holes, thereby achieving the technical effect of improving the cooling capability of the sealing unit 3 on the first end teeth 2022 .

[0074] Specifically, Figure 2 As shown, the heat conducting hole includes a first hole 501 and a second hole 502. The first hole 501 is arranged on a side of the heat conducting part 5 away from the sealing unit 3. The second hole 502 is a through hole and is arranged on a side of the heat conducting part 5.

[0075] Further, in this embodiment, taking a heat conducting portion 5 as an example, the height h of the heat conducting portion 5 is within the range of 0.2 mm-0.8 mm, the width d of the heat conducting portion 5 is within the range of 0.5×h-1.5×h, and the spacings between adjacent heat conducting portions 5 in two directions, i.e., l1 and l2, are within the range of 2×h-3×h. The diameter of the first hole 501 is within the range of 0.6×d-0.8×d, and the diameter of the second hole 502 is within the range of 0.6×h-0.8×h. Based on the design of the above parameters, the heat conducting portion 5 of this embodiment has a better cooling effect on the first end tooth 2022.

[0076] Of course, in other embodiments, the plurality of heat conducting parts 5 may be arranged in multiple rows and columns. Alternatively, heat conducting holes may be provided only on the side surfaces of the heat conducting parts 5 or on the end surfaces of the heat conducting parts 5 away from the sealing unit 3 .

[0077] In addition, preferably, a cavity 2021 is provided on one side of the blade root 202, and the cavity 2021 is provided close to the first end tooth 2022. The provision of the cavity 2021 can reduce the weight of the blade root 202, reduce the inertia force borne by the blade root 202, and improve the dynamic response and reliability of the blade root 202.

[0078] Furthermore, a second through hole 2023 is provided on the first side of the blade root 202 towards the cavity 2021 , and the second through hole 2023 is in communication with the cavity 2021 .

[0079] Based on this, the first airflow 102 can be passed through the second through hole 2023 to cool the inside of the cavity 2021 to avoid the temperature of the second compressor 2 inside the cavity 2021 affecting the cooling effect of the first end tooth 2022, thereby achieving the technical effect of improving the cooling capacity of the first end tooth 2022.

[0080] In addition, preferably, the central axis of the first through hole 205 and the straight line passing through the first through hole 205 and perpendicular to the rotating shaft form an angle with each other. At the same time, the central axis of the second through hole 2023 and the straight line passing through the second through hole 2023 and perpendicular to the rotating shaft form an angle with each other. Based on this, the speed of the first airflow 102 can be divided into a component speed along the axial direction and a component speed along the circumferential direction, so as to increase the movement time of the first airflow 102 along the circumferential direction, thereby improving the cooling effect of the first airflow 102 on the surrounding structure of the first end tooth 2022, reducing the heat energy transmitted to the first end tooth 2022 by the surrounding structure of the first end tooth 2022, and thus achieving the technical effect of improving the cooling efficiency of the first end tooth 2022.

[0081] Among them, the specific degrees of the angle between the central axis of the first through hole 205 and the straight line passing through the first through hole 205 and perpendicular to the rotating shaft, and the specific degrees of the angle between the central axis of the second through hole 2023 and the straight line passing through the second through hole 2023 and perpendicular to the rotating shaft can be adjusted according to the actual engine design, and no excessive restrictions are made here.

[0082] Specifically, the diameter of the first through hole 205 is in the range of 0.8 mm to 1.2 mm, and the diameter of the second through hole 2023 is in the range of 0.3 mm to 0.7 mm. At the same time, the number of the first through hole 205 and the second through hole 2023 is at least 72 along the circumferential direction, so that more first airflow 102 can enter the cavity 2021 and the first end tooth 2022 to improve the cooling effect of the first end tooth 2022.

[0083] In addition, in this embodiment, the engine includes:

[0084] The barrier unit 4 includes a second end tooth 4011, which is meshed with the first end tooth 2022. Along the axial direction of the rotating shaft, the sealing unit 3 at least covers the meshing ends of the second end tooth 4011 and the first end tooth 2022. Based on this, the meshing position between the second end tooth 4011 and the first end tooth 2022 can be sealed by the sealing unit 3 to prevent the second airflow 204 from flowing to the first airflow 102 through the meshing gap, increasing the temperature of the first airflow 102, and affecting the cooling effect of the first airflow 102 on the internal structure of the engine.

[0085] Wherein, the barrier unit 4 comprises:

[0086] The first blocking part 401 is sleeved on the rotating shaft at intervals, one end of the first blocking part 401 is provided with a second end tooth 4011, and the other end of the first blocking part 401 extends in a direction away from the second end tooth 4011;

[0087] The second blocking part 402 is sleeved on the rotating shaft at intervals. The second blocking part 402 is arranged close to the rotating shaft. One end of the second blocking part 402 is fixedly connected to the first blocking part 401. The gap between the second blocking part 402 and the rotating shaft is connected to the cavity 2021. The other end of the second blocking part 402 extends in a direction away from the first end tooth 2022.

[0088] The first airflow 102 flows along a side of the second blocking portion 402 close to the rotation axis, and the second airflow 204 flows along a side of the first blocking portion 401 away from the rotation axis.

[0089] By disposing the first blocking portion 401 and the second blocking portion 402, the first airflow 102 and the second airflow 204 can be blocked to prevent the first airflow 102 and the second airflow 204 from flowing along the Figure 1 As shown, mixing occurs when flowing to the right, which affects the temperature of the first airflow 102, and further affects the cooling effect of the first airflow 102 on the first end tooth 2022 and the second end tooth 4011, thereby achieving the technical effect of improving the cooling capacity of the first end tooth 2022 and the second end tooth 4011.

[0090] Furthermore, a third through hole 4012 is provided at one end of the first blocking portion 401 away from the second end tooth 4011 , and the third through hole 4012 is used to guide the second airflow 204 to a side of the second blocking portion 402 away from the rotating shaft.

[0091] The second airflow 204 can be guided toward the direction close to the rotating shaft through the third through hole 4012. Based on this, the flow direction of the first airflow 102 and the second airflow 204 in the related art is not changed. Figure 1 The position of the rightward flow as shown is adjusted, that is, the first airflow 102 and the second airflow 204 away from the second compressor 2 still flow along the original flow path in the related art, so as to achieve the technical effect of ensuring that the degree of adjustment to the engine structure is reduced.

[0092] In this embodiment, the second blocking portion 402 can be designed as a split structure along the axial direction to improve the technical effect of the simplicity of processing the second blocking portion, and the split second blocking portion 402 is fixedly connected. Of course, in other embodiments, according to different engine designs, the second blocking portion 402 is also designed as an integrated structure.

[0093] In addition, the engine of this embodiment can increase the heat transfer coefficient of the cavity 2021, the first end tooth 2022 and the second end tooth 4011 to 500W / (m 2k), so that the temperature of the first end tooth 2022 and the second end tooth 4011 of this embodiment is lower than the temperature of the first end tooth 2022 and the second end tooth 4011 in the related art, and the temperature difference is at least 50K, that is, the engine of this embodiment can effectively reduce the temperature of the first end tooth 2022 and the second end tooth 4011, thereby achieving the technical effect of increasing the service life of the first end tooth 2022 and the second end tooth 4011.

[0094] In addition, the engine includes a combustion chamber, which is sleeved outside the rotating shaft and is arranged at the end of the second compressor 2 away from the first compressor 1, that is, Figure 1 At the right end of the second compressor 2, a fourth air outlet connected to the combustion chamber is also provided on the second compressor 2. The formation of the first airflow and the second airflow is specifically as follows:

[0095] After passing through the air inlet of the first compressor 1, the air is divided into two flow paths. One flow path forms a first airflow through the first air outlet 101, and the other flow path is the first main flow path, which enters the second compressor 2 through the second air outlet. The first main flow path is then divided into two flow paths. One flow path is the second main flow path, which enters the combustion chamber through the fourth air outlet for combustion, and the other flow path forms a second airflow through the third air outlet 203.

[0096] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. An engine, characterized in that: include: Rotating shaft; a first compressor (1) rotatably connected to the rotating shaft, wherein an air inlet is provided at one end of the first compressor (1), and a first air outlet (101) and a second air outlet are provided at the other end of the first compressor (1), and air flowing out of the first air outlet (101) forms a first airflow (102); A second compressor (2) is rotatably connected to the rotating shaft and is disposed on one side of the first compressor (1). The second compressor (2) comprises a main body (201) and a blade root (202) which are connected. One end of the main body (201) is connected to the second air outlet. The other end of the main body (201) is provided with a third air outlet (203) connected to the second air outlet. Air flowing out of the third air outlet (203) forms a second air flow (204). The temperature of the second air flow (204) is higher than the temperature of the first air flow (102). ; A first side of the blade root (202) is located on the flow path of the first airflow (102), a second side of the blade root (202) is located on the flow path of the second airflow (204), an end of the blade root (202) away from the first compressor (1) is provided with a first end tooth (2022), a first through hole (205) is opened on the first side of the blade root (202) in a direction toward the first end tooth (2022), and the first through hole (205) is used to adjust the first airflow (102) to flow through the first end tooth (2022); A sealing unit (3) is provided on the inner diameter of the first end tooth (2022) and / or the outer diameter of the first end tooth (2022) and is used to isolate the first airflow (102) and the second airflow (204) on both sides of the first end tooth (2022).

2. The engine according to claim 1, characterized in that The sealing unit (3) is arranged on the inner diameter of the first end tooth (2022), and the material of the sealing unit (3) is a heat-conducting material.

3. The engine according to claim 2, characterized in that A plurality of heat-conducting parts (5) are provided on a side of the sealing unit (3) away from the first end tooth (2022), and the heat-conducting parts (5) are arranged to protrude in a direction away from the first end tooth (2022).

4. The engine according to claim 3, characterized in that The plurality of heat conducting parts (5) are arranged in a plurality of rows and columns; And / or, heat conduction holes are provided on the side surface of the heat conduction portion (5) and / or on the end surface of the heat conduction portion (5) away from the sealing unit (3).

5. The engine according to any one of claims 1 to 4, characterized in that: A cavity (2021) is provided on one side of the blade root (202), and the cavity (2021) is arranged close to the first end tooth (2022).

6. The engine according to claim 5, characterized in that A second through hole (2023) is provided on the first side of the blade root (202) in a direction toward the cavity (2021), and the second through hole (2023) is in communication with the cavity (2021).

7. The engine according to any one of claims 1 to 4, characterized in that: The central axis of the first through hole (205) forms an angle with a straight line passing through the first through hole (205) and perpendicular to the rotating shaft.

8. The engine according to claim 5, characterized in that The engine comprises: The barrier unit (4) comprises a second end tooth (4011), wherein the second end tooth (4011) is meshingly connected with the first end tooth (2022), and along the axial direction of the rotating shaft, the sealing unit (3) at least covers the meshing ends of the second end tooth (4011) and the first end tooth (2022).

9. The engine according to claim 8, characterized in that The barrier unit (4) comprises: A first blocking portion (401) is sleeved on the rotating shaft at intervals, one end of the first blocking portion (401) is provided with the second end tooth (4011), and the other end of the first blocking portion (401) extends in a direction away from the second end tooth (4011); A second blocking portion (402) is sleeved on the rotating shaft at intervals, the second blocking portion (402) is arranged close to the rotating shaft, one end of the second blocking portion (402) is fixedly connected to the first blocking portion (401), a gap between the second blocking portion (402) and the rotating shaft is communicated with the cavity (2021), and the other end of the second blocking portion (402) extends in a direction away from the first end tooth (2022); The first airflow (102) flows along a side of the second blocking portion (402) close to the rotating shaft, and the second airflow (204) flows along a side of the first blocking portion (401) away from the rotating shaft.

10. The engine according to claim 9, characterized in that A third through hole (4012) is provided at one end of the first blocking portion (401) away from the second end tooth (4011), and the third through hole (4012) is used to guide the second airflow (204) to a side of the second blocking portion (402) away from the rotating shaft.

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