A high-throughput counter-rotating turbojet engine

Abstract

The present invention belongs to the field of aeroengines, and specifically relates to a high-throughput counter-rotating turbojet engine. The engine comprises a casing, the casing including an intake casing and an exhaust casing, the casing internally provided with: an air intake system, a compressor system, a combustion chamber system, a turbine system, a tail jet system, and a transmission shaft system; the compressor system decelerates and pressurizes air flowing in through the air intake; the compressor system comprises a first rotor and a second rotor in counter-rotation; the first rotor comprises a plurality of first rotor fans, the second rotor comprises a plurality of second rotor fans, and the first and second rotor fans are spaced apart; the present invention increases air flow and enhances engine thrust by enabling the first and second rotors to rotate in counter-rotation, while ensuring a small weight and volume.

Description

Technical Field

[0001] The present invention belongs to the field of aviation engines, and in particular relates to a turbojet engine with a high-throughflow counter-rotating structure. Background Art

[0002] Turbojet engines are aircraft propulsion systems that generate thrust, enabling aircraft to overcome resistance and fly. The working principle of a turbojet engine is that the compressor is driven by a gas turbine behind the combustion chamber. The gas from the turbine expands in the tailpipe and is ejected at high speed, directly generating thrust. The thrust generated is proportional to the air flow rate passing through it.

[0003] With the development of aviation technology, the common turbojet engines currently have single-shaft and dual-shaft structures. Among them, the typical dual-shaft turbojet engine structure is as follows: Figure 1 As shown, it consists of an air inlet 1, a low-pressure compressor 2, a high-pressure compressor 3, a combustion chamber 4, a high-pressure turbine 5, a low-pressure turbine 6, an afterburner 7 and a tail nozzle 8. The compressor and turbine both include a rotor and a stator. In the working state, the rotor rotates to do work, and the stator only plays a role of rectification and pre-swirl. The high-pressure and low-pressure turbines drive the high-pressure and low-pressure compressors to work respectively.

[0004] At the same time, Chinese patent: CN113864082A provides an aviation jet engine, including a casing, the casing including an intake end and an exhaust end, and the interior of the casing is installed with: an intake duct system, a compressor system, a duct system, a combustion chamber system, a turbine system, a tail nozzle system and a transmission shaft system in sequence from the intake end to the exhaust end. The present invention is cleverly designed and novel in structure, so that the engine can obtain a high thrust-to-weight ratio or a low fuel consumption rate, and can simultaneously meet the power requirements of high maneuverability, high speed and long range of the aircraft, and has significant promotion significance.

[0005] The above-mentioned engine increases air flow by setting up a low-pressure compressor and a high-pressure compressor to achieve increased thrust and increase the aircraft's flight speed; however, such a structure increases the weight and volume of the engine, which is not conducive to increasing the aircraft's flight speed.

[0006] In view of this, the present invention is proposed. Summary of the Invention

[0007] To address the technical problems of the prior art, the present invention proposes a high-throughput counter-rotating turbojet engine. By making the first and second rotors rotate in opposite directions, the present invention increases air flow and enhances engine thrust while maintaining a small weight and volume.

[0008] The present invention includes the following technical solutions:

[0009] The present invention provides a high-throughput counter-rotating turbojet engine, comprising a casing, the casing comprising an intake casing and an exhaust casing, the interior of the casing being provided with:

[0010] an air intake system, the air intake system comprising an air intake duct through which air flows into the compressor system;

[0011] A compressor system, the compressor system decelerating and pressurizing air flowing in through the air inlet duct; the compressor system comprising a first rotor and a second rotor rotating in opposite directions;

[0012] The first rotor includes a plurality of first rotating fans, the second rotor includes a plurality of second rotating fans, and the first rotating fans and the second rotating fans are arranged at intervals;

[0013] a combustion chamber system, the combustion chamber system receiving high-pressure air from the compressor system and ejecting a first high-temperature and high-pressure combustion gas;

[0014] A turbine system, wherein the first high-temperature and high-pressure gas ejected from the combustion chamber system drives the turbine system to operate;

[0015] a tail jet system, through which the first high-temperature and high-pressure combustion gas exiting the turbine system is expanded and accelerated, thereby generating thrust;

[0016] A transmission shaft system is used to connect the turbine system and the compressor system.

[0017] Furthermore, the transmission shaft system includes a first transmission shaft and a second transmission shaft, the axial length of the first transmission shaft is greater than the axial length of the second transmission shaft, and the first transmission shaft passes through the second transmission shaft.

[0018] Furthermore, the turbine system includes a third rotor and a fourth rotor that rotate in opposite directions.

[0019] Furthermore, the third rotor includes a plurality of third rotating fans, the fourth rotor includes a plurality of fourth rotating fans, and the third rotating fans and the fourth rotating fans are arranged at intervals.

[0020] Furthermore, one end of the first transmission shaft is connected to the first rotor, and the other end is connected to the fourth rotor; one end of the second transmission shaft is connected to the second rotor, and the other end is connected to the third rotor.

[0021] Furthermore, the first rotor fan includes a first blade disk and a first working blade, and the first working blade is provided on the outer surface of the first blade disk; the second rotor fan includes a second drum and a second working blade, and the second working blade is provided on the inner surface of the second drum.

[0022] Furthermore, a plurality of first turntables are connected in sequence; and / or a plurality of second turntables are connected in sequence.

[0023] Furthermore, the third rotor fan includes a third blade disk and third working blades, and the outer surface of the third blade disk is provided with third working blades; the fourth rotor fan includes a fourth drum and fourth working blades, and the inner surface of the fourth drum is provided with fourth working blades.

[0024] Further, multiple third turntables are connected in sequence; and / or multiple fourth turntables are connected in sequence.

[0025] Furthermore, it also includes an afterburner system, which receives the incompletely burned first high-temperature and high-pressure gas ejected from the turbine system and ignites and burns it again, and the second high-temperature and high-pressure gas generated by the combustion is ejected into the tail nozzle system to generate additional thrust.

[0026] By adopting the above technical solution, the present invention has the following advantages:

[0027] 1. The present invention increases the air flow and improves the thrust of the engine while ensuring a small weight and volume by making the first rotor and the second rotor rotate in opposite directions.

[0028] 2. The counter-rotating structure of the present invention enables the stator to also perform work on the gas (i.e., the second rotor). Therefore, under the condition that the total pressure ratio remains unchanged, the structure of the engine of the present invention is more compact.

[0029] 3. The first rotor and stator (i.e., the second rotor) of the present invention can both perform work on the gas, thereby increasing the number of impeller stages that perform work, reducing the pressure ratio of a single-stage impeller, and slightly decreasing the rotational speed, which is beneficial to the life of each rotor component and bearing.

[0030] 4. The present invention greatly improves the flow capacity of the engine and the engine thrust by arranging the first rotor and the second rotor to rotate in opposite directions. It can also reduce the axial length and windward area of ​​the engine, reduce the weight of the engine, and increase its thrust-to-weight ratio, so that it can adapt to aircraft with higher thrust-to-weight ratio requirements.

[0031] 5. The present invention reduces the axial length and windward area of ​​the engine by arranging the third rotor and the fourth rotor to rotate in opposite directions, thereby reducing the weight of the engine and increasing its thrust-to-weight ratio, so that it can adapt to aircraft with higher thrust-to-weight ratio requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0033] Figure 1 It is a structural diagram of the prior art;

[0034] Figure 2 2 is a schematic structural diagram of a high-throughput counter-rotating turbojet engine according to an embodiment of the present invention;

[0035] In the accompanying drawings: 1-inlet, 2-low-pressure compressor, 3-high-pressure compressor, 4-combustion chamber, 5-high-pressure turbine, 6-low-pressure turbine, 7-afterburner, 8-tail nozzle, 10-inlet system, 20-compressor system, 210-first rotor, 211-first rotor fan, 220-second rotor, 221-second rotor fan, 30-combustion chamber system, 40-turbine system, 410-third rotor, 420-fourth rotor, 50-tail nozzle system, 60-drive shaft system, 610-first drive shaft, 620-second drive shaft, 70-afterburner system. DETAILED DESCRIPTION

[0036] The following description provides many different embodiments or examples for implementing different features of the present invention. The components and arrangements described in the following specific examples are only used to simplify the present invention and are only used as examples, not to limit the present invention.

[0037] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present invention, the meaning of "multiple" is multiple or more, unless otherwise clearly and specifically defined.

[0038] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical, electrical, or intercommunication connections; direct or indirect connections through an intermediary; and may encompass internal connectivity between multiple components or interactions between multiple components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0039] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may also include the first and second features not being in direct contact but being in contact via another feature between them. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or diagonally above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or diagonally below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0040] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings 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 making creative efforts shall fall within the scope of protection of the present invention.

[0041] like Figure 2 As shown, this embodiment provides a high-throughput counter-rotating turbojet engine, including a casing, the casing including an intake casing and an exhaust casing, and the interior of the casing is provided with:

[0042] an air intake system 10 , the air intake system 10 comprising an air intake duct through which air flows into a compressor system 20 ;

[0043] The compressor system 20 decelerates and pressurizes air flowing into the casing through the air inlet duct. The compressor system 20 includes a first rotor 210 and a second rotor 220 that rotate in opposite directions. The first rotor 210 includes a plurality of first rotor fans 211, and the second rotor 220 includes a plurality of second rotor fans 221. The first rotor fans 211 and the second rotor fans 221 are spaced apart. Counter-rotation should be understood as meaning that the first blades of the first rotor fan 211 and the second blades of the second rotor fan 221 are arranged relative to each other. The first rotor fan 211 and the second rotor fan 221 are spaced apart, which is similar to the stator rotor spaced apart arrangement in the prior art.

[0044] The first rotor 210 and the second rotor 220 may rotate in the same direction or in opposite directions. Preferably, the first rotor 210 and the second rotor 220 rotate in opposite directions.

[0045] a combustion chamber system 30 , which receives high-pressure air from the compressor system 20 and ejects a first high-temperature and high-pressure combustion gas;

[0046] The turbine system 40 is driven by the first high-temperature and high-pressure gas ejected from the combustion chamber system 30 ;

[0047] A tail jet system 50 , through which the first high-temperature and high-pressure combustion gas from the turbine system 40 is expanded and accelerated, thereby generating thrust;

[0048] The transmission shaft system 60 is used to connect the turbine system 40 and the compressor system 20 .

[0049] It should be noted that in the prior art, a stator is set in the gap of the rotor, and the stator does not rotate. However, in this application, the stator (i.e., the second rotor 220 of this application) is set to rotate, which increases the air flow and improves the thrust of the engine without increasing the volume and weight of the engine.

[0050] The compressor system 20 is disposed between the intake duct system 10 and the combustor system 30. A sealed passage is formed between the intake duct system 10, the compressor system 20, and the combustor system 30. This means that all air entering the intake duct system 10 passes through the compressor system 2020 and reaches the combustor system 30. This improves air utilization and also serves as a flow guide.

[0051] Specifically, the turntable of the second rotor 220 (which includes the multiple second drums described below) is provided with a first limiting boss on the side of the turntable proximal to the intake duct system 10, located radially outward from the intake duct system 10. Furthermore, a second limiting boss is provided on the side of the turntable proximal to the combustion chamber 310, located radially outward from the combustion chamber 310. This structure enables the second rotor 220 to rotate. A sealing ring is provided radially outward from the second rotor 220, one side of which is fixedly connected to the intake duct system 10 and the other side to the combustion chamber system 30. This creates a sealed passage between the intake duct system 10 and the compressor and combustion chamber systems 20 and 30.

[0052] Furthermore, the transmission shaft system 60 includes a first transmission shaft 610 and a second transmission shaft 620. The axial length of the first transmission shaft 610 is greater than the axial length of the second transmission shaft 620. The first transmission shaft 610 passes through the second transmission shaft 620 (i.e., the first transmission shaft 610 is disposed within the second transmission shaft 620). The first transmission shaft 610 and the second transmission shaft 620 are preferably coaxially disposed.

[0053] Furthermore, the turbine system 40 includes a counter-rotating third rotor 410 and a fourth rotor 420. Based on this, it has the advantages of reducing the axial length and windward area of ​​the engine and reducing the weight of the engine. Counter-rotation should be understood as the third blades of the third rotor and the fourth blades of the fourth rotor being arranged relative to each other; the third rotor 410 and the fourth rotor 420 can rotate in the same direction or in different directions. Preferably, the third rotor 410 and the fourth rotor 420 rotate in different directions; it should be noted that the direction of rotation of the first rotor 210 and the direction of rotation of the fourth rotor 420 are the same, and the direction of rotation of the second rotor 220 and the third rotor 410 are the same.

[0054] Furthermore, the third rotor 410 includes a plurality of third rotor fans, and the fourth rotor 420 includes a plurality of fourth rotor fans, and the third rotor fans and the fourth rotor fans are arranged at intervals.

[0055] Furthermore, one end of the first transmission shaft 610 is connected to the first rotor 210 , and the other end is connected to the fourth rotor 420 ; one end of the second transmission shaft 620 is connected to the second rotor 220 , and the other end is connected to the third rotor 410 .

[0056] Furthermore, the first rotary fan 211 includes a first blade disk and a first working blade, and the first working blade is provided on the outer surface of the first blade disk; the second rotary fan 221 includes a second drum and a second working blade, and the second working blade is provided on the inner surface of the second drum.

[0057] Further, a plurality of first blade disks are connected in sequence; and / or a plurality of second drums are connected in sequence.

[0058] Preferably, the plurality of first blade disks are integrally formed; and / or the plurality of second drums are integrally formed; based on this, the structure of the rotor is made more stable.

[0059] Furthermore, the third rotor fan includes a third blade disk and third working blades, and the outer surface of the third blade disk is provided with third working blades; the fourth rotor fan includes a fourth drum and fourth working blades, and the inner surface of the fourth drum is provided with fourth working blades.

[0060] Further, a plurality of third blade disks are connected in sequence; and / or a plurality of fourth blade disks are connected in sequence.

[0061] Preferably, the plurality of third blade disks are integrally formed, and / or the plurality of fourth blade disks are integrally formed; thereby making the rotor structure more stable.

[0062] Furthermore, the engine also includes an afterburner system 70, which receives the incompletely burned first high-temperature, high-pressure gas ejected from the turbine system 40 and re-ignites it. The resulting second high-temperature, high-pressure gas is then ejected into the tailpipe system to generate additional thrust. This re-combustion in the afterburner system 70 allows unburned oxygen in the combustion chamber system 30 to participate in combustion again, avoiding oxygen waste and increasing engine thrust.

[0063] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A high-throughput counter-rotating turbojet engine, characterized in that: The casing comprises an air intake casing and an exhaust casing, and the interior of the casing is provided with: An air intake system (10), the air intake system (10) comprising an air intake, through which air flows into the compressor system (20); A compressor system (20), the compressor system (20) decelerating and pressurizing air flowing in through an air inlet; the compressor system (20) comprising a first rotor (210) and a second rotor (220) that rotate in opposite directions; The first rotor (210) includes a plurality of first rotating fans (211), and the second rotor (220) includes a plurality of second rotating fans (221), wherein the first rotating fans (211) and the second rotating fans (221) are arranged at intervals; a combustion chamber system (30), the combustion chamber system (30) receiving high-pressure air from the compressor system (20) and ejecting a first high-temperature and high-pressure combustion gas; A turbine system (40), wherein the first high-temperature and high-pressure gas ejected from the combustion chamber system (30) drives the turbine system (40) to operate; A tail jet system (50), wherein the first high-temperature and high-pressure combustion gas exiting the turbine system (40) is expanded and accelerated through the tail jet system (50), thereby generating thrust; a transmission shaft system (60), the transmission shaft system (60) being used to connect the turbine system (40) and the compressor system (20); The transmission shaft system (60) comprises a first transmission shaft (610) and a second transmission shaft (620), the axial length of the first transmission shaft (610) is greater than the axial length of the second transmission shaft (620), and the first transmission shaft (610) passes through the second transmission shaft (620); The turbine system (40) includes a third rotor (410) and a fourth rotor (420) that rotate in opposite directions; the third rotor (410) includes a plurality of third rotor fans, the fourth rotor (420) includes a plurality of fourth rotor fans, and the third rotor fans and the fourth rotor fans are arranged at intervals; The system also includes an afterburner system (70), which receives the first high-temperature and high-pressure gas that is not fully burned and is ejected from the turbine system (40) and ignites and burns it again, and the second high-temperature and high-pressure gas generated by the combustion is ejected to the tail nozzle system to generate additional thrust.

2. A high-throughput counter-rotating turbojet engine according to claim 1, characterized in that: One end of the first transmission shaft (610) is connected to the first rotor (210), and the other end is connected to the fourth rotor (420); one end of the second transmission shaft (620) is connected to the second rotor (220), and the other end is connected to the third rotor (410).

3. A high-throughput counter-rotating turbojet engine according to claim 1 or 2, characterized in that: The first rotating fan (211) comprises a first blade disk and a first working blade, and the first working blade is provided on the outer surface of the first blade disk; the second rotating fan (221) comprises a second drum and a second working blade, and the second working blade is provided on the inner surface of the second drum.

4. A high-throughput counter-rotating turbojet engine according to claim 3, characterized in that: A plurality of first turntables are connected in sequence; and / or a plurality of second turntables are connected in sequence.

5. The high-throughput counter-rotating turbojet engine according to claim 3, characterized in that: The third rotor fan includes a third blade disk and third working blades, and the outer surface of the third blade disk is provided with third working blades; the fourth rotor fan includes a fourth drum and fourth working blades, and the inner surface of the fourth drum is provided with fourth working blades.

6. A high-throughput counter-rotating turbojet engine according to claim 5, characterized in that: A plurality of third turntables are connected in sequence; and / or a plurality of fourth turntables are connected in sequence.

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