Oxygen-enriched turbine engine based on bleed air cooling technology

Abstract

The invention relates to the technical field of turbine engines, in particular to an oxygen-enriched turbine engine based on a bleed air cooling technology, which comprises a rotating shaft mechanism, one end of the rotating shaft mechanism is connected with an air compressor impeller through a spline, and a cold source introduction mechanism for sucking cold air as a cold source is arranged in the air compressor impeller. A turbine disc mechanism is movably installed at the other end of the rotating shaft mechanism, the cold source introduction mechanism comprises an air entraining opening formed in the air compressor impeller, an air mixing annular cavity is formed in the air compressor impeller and communicates with the interior of the air entraining opening, and a cooling channel is formed in the spline. The turbine disc mechanism is arranged, the cooling inner groove and the cooling channel are matched with each other, cold air can circularly flow in the compressor impeller and the turbine disc, so that the turbine disc is rapidly cooled, the cooling effect is good, the air entraining channels are formed in the impeller and the turbine and are integrated with an engine, and the cooling effect is good. And extra space is not occupied.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine engines, and in particular to an oxygen-rich turbine engine based on bleed air cooling technology. Background Art

[0002] Oxygen-enriched turbo rocket engines, also called air-breathing rocket engines, can capture oxygen from the denser atmosphere of near-Earth space, and can achieve long-term high-speed cruising and maneuvering flight in near-Earth space at a wide Mach number. However, during the flight, the engine turbine components will always be in a high-temperature and high-speed environment. In order to prevent the temperature of the turbine itself from being too high, causing over-temperature of the turbine components, the turbine needs to be cooled to ensure the safety and reliability of the engine.

[0003] In the prior art, in order to quickly dissipate heat and cool the engine turbine, it is usually necessary to carry an additional cold source inside the engine, which not only increases the weight of the engine, but also requires additional power for the cold source, which will shorten the engine's endurance to a certain extent. Summary of the invention

[0004] In view of the shortcomings of the prior art, the present invention provides an oxygen-rich turbine engine based on bleed air cooling technology, which solves the technical problem that in order to cool the turbine in the prior art, an additional cold source needs to be carried inside the engine, which increases the weight of the engine and affects the endurance. The engine has the advantage of being able to use the cold air in the low-altitude environment as a cold source without the need to carry an additional cold source.

[0005] To solve the above technical problems, the present invention provides the following technical solutions: an oxygen-rich turbine engine based on bleed air cooling technology, comprising a rotating shaft mechanism, one end of the rotating shaft mechanism is connected to a compressor impeller through a spline, a cold source introduction mechanism for sucking cold air as a cold source is provided inside the compressor impeller, a turbine disk mechanism is movably installed on the other end of the rotating shaft mechanism, the cold air compressed by the compressor impeller will enter the interior of the turbine disk mechanism through the rotating shaft mechanism, thereby dissipating heat and cooling the turbine disk mechanism, and then the cold source gas that has completed the heat exchange will be discharged to the outside through the rotating shaft mechanism, the cold source introduction mechanism includes an air inlet opened on the compressor impeller, a mixing annular cavity is opened inside the compressor impeller, the mixing annular cavity is connected to the interior of the air inlet, a cooling channel is opened inside the spline, after the cold air enters the interior of the compressor impeller through the air inlet, it will be mixed in the interior of the mixing annular cavity, and then enter the interior of the rotating shaft mechanism through the cooling channel.

[0006] Preferably, a number of air inlets are provided at equal intervals, and the number of cooling channels is less than the number of air inlets. After the compressed air is mixed inside the mixing ring cavity, it will evenly enter the interior of the rotating shaft mechanism under the action of multiple cooling channels.

[0007] Preferably, the rotating shaft mechanism includes an internally hollow rotating shaft body, the hollow portion of the rotating shaft body is divided into an air inlet channel and an air outlet channel, the air inlet channel and the air outlet channel are not connected to each other, and an exhaust port connected to the air outlet channel is opened at the end of the rotating shaft body, and after the cooling air enters the air outlet channel, it will be discharged into the atmosphere through the exhaust port.

[0008] Preferably, the contact angle between the cooling channel and the rotating shaft body is forty-five degrees, and the cooling channel is connected to the air intake channel. When the compressor impeller is running, cold air in the atmosphere will enter the interior of the air intake channel through the cooling channel.

[0009] Preferably, the turbine disc mechanism includes a turbine disc body, a cold source inlet is provided inside the turbine disc body, the cold source inlet is connected to the air intake passage, a cooling inner groove is provided inside the turbine disc body, after the cold air enters the air intake passage, it will enter the cooling inner groove through the cold source inlet, thereby cooling and dissipating the heat of the turbine disc body.

[0010] Preferably, a cold source outlet communicated with the air outlet passage is provided inside the turbine disc body, and the cold source outlet is communicated with the air outlet passage.

[0011] Preferably, the cooling inner tank is U-shaped, one end of the cooling inner tank is connected to the cold source inlet, and the other end of the cooling inner tank is connected to the cold source outlet. After the cold air enters the cooling inner tank through the cold source inlet, it will be discharged through the cold source outlet, so that the cold air continuously flows through the interior of the cooling inner tank.

[0012] Preferably, the cold source inlet, the cooling inner groove and the cold source outlet are all provided in several groups, which can effectively ensure the efficiency of cooling the turbine disk.

[0013] By means of the above technical solution, the present invention provides an oxygen-enriched turbine engine based on bleed air cooling technology, which has at least the following beneficial effects:

[0014] 1. The present invention provides a cold source introduction mechanism and utilizes the cooperation between the air inlet and the compressor impeller to utilize the cold air in the low-altitude environment as a cold source. There is no need to carry an additional cold source, the material is simple, and the engine weight can be reduced to a certain extent without affecting the engine's endurance.

[0015] 2. The present invention arranges a cold source introduction mechanism and evenly opens a plurality of air inlets at the axial center of the impeller blades, so that the air has a certain high pressure, which can provide power for the air flow. There is no need to provide an additional power source for the cold source, and the weight of the engine can also be reduced.

[0016] 3. The present invention sets a turbine disk mechanism and utilizes the mutual cooperation between the cooling inner groove and the cooling channel to enable cold air to circulate inside the compressor impeller and the turbine disk, thereby quickly cooling the turbine disk with good cooling effect. Moreover, the air induction channels are opened inside the impeller and the turbine, and are integrated with the engine, so no additional space is occupied.

[0017] 4. The present invention provides a turbine disc mechanism, so that the air flow rate used for bleed air only accounts for 0.5% of the total air flow rate, and the impact on the air flow rate required by the combustion chamber is negligible, which will not have a negative impact on the power performance of the engine and can effectively ensure the reliability of the engine.

[0018] 5. The present invention provides a rotating shaft mechanism and opens an air inlet channel and an air outlet channel which are not communicated with each other inside the rotating shaft body, so that the air after cooling can be quickly discharged into the atmosphere, thereby ensuring the normal cooling process. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0020] Figure 1 It is a front view of the overall structure of the present invention;

[0021] Figure 2 A top view of the overall structure of the present invention;

[0022] Figure 3 It is a structural schematic diagram of the cold source introduction mechanism in the present invention;

[0023] Figure 4 It is a cross-sectional view of the overall structure of the present invention;

[0024] Figure 5 It is a schematic structural diagram of the turbine disc mechanism in the present invention.

[0025] In the figure: 1. compressor impeller; 2. cold source introduction mechanism; 201. air inlet; 202. mixing annular cavity; 203. cooling channel; 3. rotating shaft mechanism; 301. air inlet channel; 302. air outlet channel; 303. exhaust port; 4. turbine disk mechanism; 401. cold source inlet; 402. cooling inner groove; 403. cold source outlet. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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 ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] Embodiment 1

[0028] In order to quickly dissipate heat and cool the engine turbine in the prior art, it is usually necessary to carry an additional cooling source inside the engine, which not only increases the weight of the engine, but also requires additional power for the cooling source, which will shorten the engine's cruising time to a certain extent. In order to solve this technical defect in the prior art, such as Figure 1-Figure 4 As shown, this embodiment proposes an oxygen-rich turbine engine based on bleed air cooling technology, which can use the pressure of the cold air itself as power, without the need to provide an additional power source for cooling. One end of the engine shaft mechanism 3 is connected to the compressor impeller 1 through a spline, and the interior of the compressor impeller 1 is provided with a cold source introduction mechanism 2 for sucking cold air as a cold source. The other end of the shaft mechanism 3 is movably mounted with a turbine disk mechanism 4. The cold air compressed by the compressor impeller 1 will enter the interior of the turbine disk mechanism 4 through the shaft mechanism 3, thereby dissipating heat and cooling the turbine disk mechanism 4. Subsequently, the cold source gas that has completed the heat exchange will be discharged to the outside through the shaft mechanism 3.

[0029] In order to use cold air as a cold source to reduce the weight of the engine, the present embodiment is provided with a cold source introduction mechanism 2. Specifically, the cold source introduction mechanism 2 includes an air inlet 201 opened on the compressor impeller 1, and an air mixing annular cavity 202 is opened inside the compressor impeller 1. The air mixing annular cavity 202 is connected to the inside of the air inlet 201, and a cooling channel 203 is opened inside the spline. After the cold air enters the interior of the compressor impeller 1 through the air inlet 201, it will be mixed inside the air mixing annular cavity 202, and then enter the interior of the rotating shaft mechanism 3 through the cooling channel 203. A number of air inlets 201 are opened at equal intervals, and the number of cooling channels 203 is less than the number of air inlets 201. After the compressed air is mixed inside the air mixing annular cavity 202, it will evenly enter the interior of the rotating shaft mechanism 3 under the action of multiple cooling channels 203.

[0030] According to the above content, when the engine is working, the cold air compressed by the compressor impeller 1 will enter the interior of the mixing annular cavity 202 through multiple air inlets 201, and Figure 3 As shown, there are fourteen air inlets 201, which are in the same axial position, all at the axial center of the impeller blades. The air at this position has a certain high pressure, which can be used as a driving force for the airflow. In addition, the air temperature at this position has not yet risen, so it can be used as a cold source.

[0031] Subsequently, the cold air is mixed inside the mixing ring cavity 202 and then enters the interior of the intake passage 301 through the cooling passage 203 inside the spline.

[0032] The present embodiment sets a cold source introduction mechanism 2, and utilizes the mutual cooperation between the air inlet 201 and the compressor impeller 1, so that the cold air in the low-altitude environment can be used as a cold source. There is no need to carry an additional cold source, and the material is simple. The weight of the engine can be reduced to a certain extent without affecting the engine's endurance. Moreover, the present embodiment sets a cold source introduction mechanism 2, and multiple air inlets 201 are evenly opened at the axial center of the impeller blades, so that the air has a certain high pressure, which can provide power for the airflow. There is no need to provide an additional power source for the cold source, which can also reduce the weight of the engine.

[0033] Embodiment 2

[0034] In order to prevent the engine turbine parts from overheating, based on the first embodiment, Figure 1 , Figure 2 , Figure 4 as well as Figure 5 As shown, the present embodiment is provided with a shaft mechanism 3 and a turbine disk mechanism 4. Specifically, the shaft mechanism 3 includes a shaft body with a hollow interior. The contact angle between the cooling channel 203 and the shaft body is forty-five degrees. The cooling channel 203 is connected to the air inlet channel 301. When the compressor impeller 1 is running, the cold air in the atmosphere will enter the interior of the air inlet channel 301 through the cooling channel 203. The hollow portion of the shaft body is divided into an air inlet channel 301 and an air outlet channel 302. The air inlet channel 301 and the air outlet channel 302 are not connected to each other. An exhaust port 303 connected to the air outlet channel 302 is provided at the end of the shaft body. After the cooled air enters the air outlet channel 302, it will be discharged into the atmosphere through the exhaust port 303.

[0035] The turbine disc mechanism 4 includes a turbine disc body, a cold source inlet 401 is provided inside the turbine disc body, and the cold source inlet 401 is connected to the air inlet channel 301. A cooling inner groove 402 is provided inside the turbine disc body. After the cold air enters the air inlet channel 301, it will enter the cooling inner groove 402 through the cold source inlet 401, thereby cooling and dissipating the turbine disc body. A cold source outlet 403 connected to the air outlet channel 302 is provided inside the turbine disc body, and the cold source outlet 403 is connected to the air outlet channel 301. 302 is connected, the cooling inner groove 402 is U-shaped, one end of the cooling inner groove 402 is connected to the cold source inlet 401, and the other end of the cooling inner groove 402 is connected to the cold source outlet 403. After the cold air enters the cooling inner groove 402 through the cold source inlet 401, it will be discharged through the cold source outlet 403, so that the cold air continuously flows through the inside of the cooling inner groove 402. The cold source inlet 401, the cooling inner groove 402 and the cold source outlet 403 are all provided with several groups, which can effectively ensure the efficiency of cooling the turbine disk.

[0036] According to the above content, it can be known that after the cold air enters the air intake channel 301, it will enter the interior of the cooling inner groove 402 through the cold source inlet 401, and enter the interior of the air outlet channel 302 through the cold source outlet 403, so that the cold air flows in multiple cooling inner grooves 402. During the flow process, the heat on the turbine disk body will be taken away, thereby achieving rapid cooling.

[0037] Next, the cold air that has finished cooling will be discharged to the outside through the air outlet channel 302 and the air outlet 303.

[0038] Moreover, through a large number of experimental studies, we have found that the air entering the air inlet 201 on the compressor impeller 1 for cooling only accounts for 0.5% of the total air flow on the compressor impeller 1. Therefore, the impact on the air flow on the compressor impeller 1 can be ignored, and will not affect the process of air entering the combustion chamber for combustion, nor will it have a negative impact on the power performance of the engine.

[0039] In this embodiment, by setting a turbine disk mechanism 4, the mutual cooperation between the cooling inner groove 402 and the cooling channel 203 can be used to make the cold air circulate inside the compressor impeller 1 and the turbine disk, so as to quickly cool the turbine disk, and the cooling effect is good. Moreover, the air induction channels are opened inside the impeller and the turbine, and are integrated with the engine, and do not occupy additional space. In addition, in this embodiment, by setting the turbine disk mechanism 4, the air flow rate used for the induction air only accounts for 0.5% of the total air flow rate, and the influence on the air flow rate required by the combustion chamber can be ignored, and it will not have a negative impact on the power performance of the engine, and can effectively ensure the reliability of the engine. Moreover, in this embodiment, by setting the shaft mechanism 3, an air inlet channel 301 and an air outlet channel 302 that are not connected to each other are opened inside the shaft body, so that the air that has finished cooling can be quickly discharged into the atmosphere, thereby ensuring the normal progress of the cooling.

[0040] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0041] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An oxygen-rich turbine engine based on bleed air cooling technology, comprising a shaft mechanism (3), characterized in that: One end of the rotating shaft mechanism (3) is connected to a compressor impeller (1) via a spline, a cold source introduction mechanism (2) for sucking cold air as a cold source is provided inside the compressor impeller (1), and a turbine disk mechanism (4) is movably mounted on the other end of the rotating shaft mechanism (3); The cold source introduction mechanism (2) comprises an air inlet (201) provided on the compressor impeller (1), an air mixing annular cavity (202) provided inside the compressor impeller (1), the air mixing annular cavity (202) being connected to the inside of the air inlet (201), and a cooling channel (203) provided inside the spline.

2. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 1, characterized in that: A plurality of air inlets (201) are arranged at equal intervals, and the number of cooling channels (203) is less than the number of air inlets (201).

3. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 1, characterized in that: The rotating shaft mechanism (3) comprises a rotating shaft body with a hollow interior, wherein the hollow portion of the rotating shaft body is divided into an air inlet channel (301) and an air outlet channel (302), the air inlet channel (301) and the air outlet channel (302) are not connected to each other, and an exhaust port (303) connected to the air outlet channel (302) is provided at the end of the rotating shaft body.

4. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 3, characterized in that: The contact angle between the cooling channel (203) and the rotating shaft body is forty-five degrees, and the cooling channel (203) is connected to the air intake channel (301).

5. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 1, characterized in that: The turbine disc mechanism 3 comprises a turbine disc body, a cold source inlet (401) is provided inside the turbine disc body, the cold source inlet (401) is connected to the air intake channel (301), and a cooling inner groove (402) is provided inside the turbine disc body.

6. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 5, characterized in that: A cold source outlet (403) communicating with the air outlet channel (302) is provided inside the turbine disc body.

7. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 5, characterized in that: The cooling inner groove (402) is U-shaped, one end of the cooling inner groove (402) is connected to the cold source inlet (401), and the other end of the cooling inner groove (402) is connected to the cold source outlet (403).

8. The oxygen-rich turbine engine based on bleed air cooling technology according to claim 6, characterized in that: The cold source inlet (401), the cooling inner tank (402) and the cold source outlet (403) are all provided in a plurality of groups.

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