A rotary ramjet turbofan engine

Abstract

The application provides a rotary ram shock wave supercharged gas turbine engine and belongs to the technical field of turbine engines, which comprises an outer casing and an inner casing, an outer channel is formed between the inner casing and the outer casing, a guide vane is installed in the outer casing and is used for guiding airflow, a first mechanism is installed in the inner casing and is used for supercharging and heating the airflow and doing work, a second mechanism is arranged on one side of the inner casing and is used for supercharging and heating the airflow for the second time. The application solves the problems of large windward area of the centrifugal compressor, many parts of the multistage axial flow compressor and low efficiency of small flow by using the rotary ram compressor, higher flow and pressure ratio are obtained in compact size, greater thrust is obtained under the condition of smaller outer size of the original engine, the outer size is reduced by about 32%, and the thrust is increased by 17.3% under the condition of the same fuel consumption rate when the engine is at rest.

Description

Technical Field

[0001] This invention belongs to the field of turbine engine technology, and specifically relates to a rotary ramjet shockwave supercharged gas turbine engine. Background Technology

[0002] The centrifugal configuration widely used in small turbojet engines has the drawback of a large frontal area, which leads to a sharp increase in drag during high-speed flight. If a multi-stage axial compressor is used, it has a large number of parts, and its efficiency is relatively low at low flow rates. During high-speed flight, the inlet ramjet effect intensifies, and the increased compressor inlet temperature leads to thermal throttling and reduced cycle net power in conventional engines, resulting in a rapid drop in thrust. Summary of the Invention

[0003] To address the above problems, this invention proposes a rotary ramjet shockwave supercharged gas turbine engine.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] A rotary ramjet shockwave supercharged gas turbine engine includes an outer casing and an inner casing, wherein the inner casing is located inside the outer casing and an outer bypass duct is formed between the inner casing and the outer casing;

[0006] The outer casing is equipped with guide vanes, which are used to guide airflow.

[0007] The inner casing is equipped with a first mechanism, which is used to pressurize and heat the airflow and perform work.

[0008] A second mechanism is also provided on one side of the inner casing, which is used to perform secondary pressurization and heating of the airflow.

[0009] Preferably, the outer casing is provided with a front section, a middle section and a rear section;

[0010] The guide vane is located at the front opening;

[0011] The inner casing is located in the front section and on one side of the guide vanes, while the second mechanism is located in the middle section;

[0012] The rear section is a binary tail nozzle, which is used to adjust the pipe diameter to a first pipe diameter or a second pipe diameter.

[0013] The first pipe diameter is a pipe diameter that first decreases in size along the axial direction of the outer casing, and then increases in size again.

[0014] The second pipe diameter is the pipe diameter that decreases from large to small along the axial direction of the outer casing.

[0015] Preferably, the first mechanism includes a rotary ram compressor, a first combustion chamber, and a second turbine;

[0016] The rotary ram compressor is connected to the second turbine;

[0017] The first combustion chamber is located between the rotary ram compressor and the second turbine.

[0018] Preferably, the first combustion chamber is further connected to a delivery pipe, which is used to deliver fuel into the first combustion chamber.

[0019] Preferably, the second mechanism includes a second combustion chamber;

[0020] The second combustion chamber is connected to a conduit, which is connected to a delivery pipeline.

[0021] Preferably, a plurality of mode switching valves are installed on the side of the inner casing near the guide vanes, and the mode switching valves are used to guide the airflow.

[0022] Preferably, a duct ejector is installed on the inner wall of the outer casing, the duct ejector being used to guide the airflow passing through the outer duct to the second mechanism.

[0023] Preferably, the second turbine is connected to a rotary ram compressor via a shaft, and the rotary ram compressor is connected to guide vanes via a shaft.

[0024] Preferably, the inner casing surface is further provided with a vent hole, the position of which corresponds to the rotary ram compressor.

[0025] Preferably, the outer casing and the inner casing are coaxially arranged.

[0026] The beneficial effects of this invention are:

[0027] 1. This invention utilizes a rotary ram compressor to solve the problems of large frontal area of ​​centrifugal compressors and numerous parts and low efficiency of multi-stage axial compressors at low flow rates. It achieves higher flow rate and pressure ratio in a compact size, ensuring that the original engine obtains greater thrust with a smaller external dimension. Compared with a certain engine of the same class, after using a rotary ram compressor, it can achieve a pressure ratio of 5 orders of magnitude in a single stage, while reducing the external dimension by about 32%, and increasing the thrust by 17.3% at the same fuel consumption rate when stationary.

[0028] 2. This invention employs a series-connected combined power scheme, utilizing rotary ramjet boosting at low speeds and ramjet effect to boost airflow at high speeds. This solves the problems of thermal throttling and reduced cycle power in traditional engines above Mach 3, significantly increasing engine thrust at high Mach numbers. After mode switching, the thrust at Ma=3 is 9.5 times that of a conventional engine of the same magnitude.

[0029] 3. By using a mode switching valve and a ducted ejector, the present invention adjusts the working mode of the gas turbine engine to a high-speed mode and a low-speed mode, thereby improving working efficiency.

[0030] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 A schematic diagram of an existing gas turbine engine using a single centrifugal compressor is shown.

[0033] Figure 2 A schematic diagram of an existing gas turbine engine using a multi-stage axial compressor is shown.

[0034] Figure 3 A schematic diagram of a rotary ram-shock supercharged gas turbine engine according to the present invention is shown;

[0035] Figure 4 An airflow diagram of the gas turbine engine of the present invention in low-speed mode is shown;

[0036] Figure 5 An airflow diagram of the gas turbine engine of the present invention in high-speed mode is shown;

[0037] Figure 6 A comparison diagram of the inner casing of the present invention and a certain turbojet engine is shown.

[0038] In the diagram: 1. First casing; 101. Single centrifugal compressor; 102. Working combustion chamber; 103. Drive shaft; 104. First turbine; 105. Nozzle; 2. Second casing; 201. Multi-stage axial compressor; 3. Outer casing; 301. Guide vane; 302. Bypass ejector; 303. Two-dimensional tail nozzle; 304. Outer bypass; 4. Inner casing; 401. Mode conversion valve; 402. Rotary ram compressor; 4021. Adjustable guide vane; 4022. Rotary ram rotor; 4023. Stator; 403. First combustion chamber; 404. Second turbine; 4041. Turbine guide vane; 4042. Turbine rotor; 405. Duct; 406. Second combustion chamber; 407. Drain hole. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] A rotating ramjet shockwave supercharged gas turbine engine, such as Figure 3 As shown, it includes an outer casing 3 and an inner casing 4, which are coaxially arranged. The inner casing 4 is located inside the outer casing 3, and the inner casing 4 and the outer casing 3 form an outer bypass 304; Figure 3 The outer casing 3 is provided with a front section, a middle section and a rear section. A guide vane 301 is installed at the opening of the front section. The function of the guide vane 301 is to guide the airflow into the interior of the outer casing 3.

[0041] Additionally, the inner casing 4 is located in the front section and on one side of the guide vane 301, the second mechanism is located in the middle section, and the rear section is the two-dimensional tail nozzle 303, the diameter of which can be adjusted according to the operating mode. The operating modes of this invention can be divided into high-speed mode and low-speed mode. In high-speed mode, the diameter of the two-dimensional tail nozzle 303 changes from large to small and then from small to large; in low-speed mode, the diameter of the two-dimensional tail nozzle 303 changes from large to small.

[0042] In addition, a first mechanism is installed inside the inner casing 4. This first mechanism is used to pressurize and heat the airflow and perform work. Specifically, the first mechanism includes a rotary ram compressor 402, a first combustion chamber 403, and a second turbine 404. The first combustion chamber 403 is located between the rotary ram compressor 402 and the second turbine 404. The second turbine 404 is connected to the rotary ram compressor 402 via a shaft, and the rotary ram compressor 402 is connected to the guide vanes 301 via a shaft. In operation, the second turbine 404, the rotary ram compressor 402, and the guide vanes 301 rotate at high speed, allowing external airflow to enter.

[0043] It should be noted that, as Figure 1 The diagram shows a conventional gas turbine engine with a single centrifugal compressor, including a first housing 1, a single centrifugal compressor 101, a working combustion chamber 102, a drive shaft 103, a first turbine 104, and a nozzle 105. The single centrifugal compressor 101 and the first turbine 104 are connected by the drive shaft 103, the working combustion chamber 102 is located between the single centrifugal compressor 101 and the first turbine 104, and the nozzle 105 is located at the rear of the first housing 1. Figure 1 The centrifugal configuration used in the structure has the drawback of a large frontal area, which leads to a sharp increase in drag during high-speed flight. After being pressurized by a single centrifugal compressor 101, the airflow enters the combustion chamber 102, where combustion takes place. The high-temperature, high-pressure gas from combustion enters the first turbine 104, where the airflow expands and performs work. The turbine, via a drive shaft 103, drives the compressor to rotate at high speed to continue drawing in gas. Simultaneously, the gas that has performed work enters the nozzle 105 for further expansion and acceleration, and is then ejected at high speed from the nozzle 105, generating thrust. Additionally... Figure 2 The diagram shown is a schematic of a gas turbine engine with an existing multi-stage axial compressor 201, which is similar to... Figure 1 The difference lies in replacing the first casing 1 with the second casing 2, and replacing the single centrifugal compressor 101 with a multi-stage axial compressor 201, but... Figure 2 The structure uses many parts, and the efficiency of the multi-stage axial compressor 201 is relatively low at low flow rates.

[0044] Furthermore, the first combustion chamber 403 is also connected to a delivery pipe for delivering fuel into the first combustion chamber 403. The combustion of the fuel in the first combustion chamber 403 generates high temperatures, which heat the airflow. Additionally, a second mechanism is provided on one side of the inner casing 4. This second mechanism is used for secondary pressurization and heating of the airflow. The second mechanism includes a second combustion chamber 406, which is connected to a conduit 405, which is connected to the delivery pipe.

[0045] It should be noted that, through Figure 3It is known that external fuel is supplied to the first combustion chamber 403 and the second combustion chamber 406 through the delivery pipe and conduit 405. The purpose of using two combustion chambers is to achieve multi-stage heating of the airflow.

[0046] Furthermore, several mode switching valves 401 are installed on the side of the inner casing 4 near the guide vanes 301. The mode switching valves 401 are used to guide the airflow. A ducted ejector 302 is installed on the inner wall of the outer casing 3. The ducted ejector 302 is used to guide the airflow passing through the outer duct 304 to the second mechanism.

[0047] It should be noted that the function of the modal switching valve 401 of the present invention is to close or open the air inlet of the inner casing 4. Figure 3 When the mode switching valve 401 is closed, the airflow cannot enter the inner casing 4, but enters the outer bypass duct 304. Conversely, when the mode switching valve 401 is opened, the outer bypass duct 304 will be closed, and the airflow will enter the inner casing 4.

[0048] Furthermore, a vent hole 407 is provided on the surface of the inner casing 4, and the position of the vent hole 407 corresponds to the rotary ram compressor 402.

[0049] It should be noted that the vent 407 can be opened and closed as needed. When the aircraft is flying at low speed, the vent 407 is closed, and the pressurization is mainly achieved by rotating the ram compressor at 402. When the aircraft is in the transition state between high and low speed (Mach number 1.5-2), the vent 407 is opened to alleviate the thermal blockage effect of the compressor. When the aircraft accelerates to high speed, it relies entirely on the ram action for pressurization, and the vent 407 is closed at this time.

[0050] like Figure 4 and Figure 5 As shown, the rotary ram compressor 402 of the present invention specifically includes an adjustable guide vane 4021, a rotary ram rotor 4022 and a stator 4023, while the vent hole 407 faces the rotary ram rotor 4022, and the second turbine 404 includes a turbine guide vane 4041 and a turbine rotor 4042.

[0051] The following describes the two operating modes of the rotary ramjet shockwave supercharged gas turbine engine of the present invention:

[0052] Low speed mode: such as Figure 4As shown, the guide vane 301 guides the airflow into the outer casing 3. The mode conversion valve 401 is opened and the duct ejector 302 is closed. The airflow is guided by the mode conversion valve 401 into the rotary ram compressor 402 for pressurization, and then enters the first combustion chamber 403 for combustion to form high-temperature and high-pressure gas, which enters the second turbine 404 to do work. Then the airflow enters the second combustion chamber 406 and is finally discharged through the two-dimensional tail nozzle 303. At this time, the two-dimensional tail nozzle 303 adopts a structure in which the pipe diameter decreases from large to small.

[0053] High-speed mode: such as Figure 5 As shown, the mode conversion valve 401 is closed and the duct ejector 302 is open. At high speed, the airflow mainly passes through the guide vane 301 and is guided by the mode conversion valve 401 to the outer duct 304 for ram boosting before entering the second combustion chamber 406 for combustion. Then, it is discharged through the two-dimensional tail nozzle 303. At this time, the diameter of the two-dimensional tail nozzle 303 changes from large to small and then from small to large. The ram effect is used to boost the airflow, solving the problems of thermal throttling and reduced cycle net power of traditional engines above Mach 3.

[0054] like Figure 6 The table below shows a comparison between the first structure of this invention and a certain turbojet engine.

[0055] Table 1: Comparison results when H=0m and Ma=0

[0056]

[0057]

[0058] As shown in Table 1, when H = 0m and Ma = 0, the internal thrust of the rotary ram compressor 402 of the present invention increases by 17.3%, the fuel consumption rate remains unchanged, and the external profile decreases by 32%.

[0059] Table 2: Comparison of results when H=10000m and Ma=3

[0060]

[0061]

[0062] As can be seen from Table 2, the stamping calculation of the present invention is 9.5 times the thrust under normal conditions.

[0063] This invention integrates shock wave compression and conventional compressor design technologies, drawing inspiration from the pressurization method of supersonic inlets. Through high-speed rotation, the airflow reaches a Mach number of 2 or higher relative to the rotating impeller. At this point, the channel contracts, creating a series of weakly oblique shock waves. The pressurization of this shock wave system results in a highly efficient compression system with a single-stage pressure ratio far exceeding that of conventional compressors. The rotary ram compressor 402 solves the problems of large frontal area in centrifugal compressors and numerous parts and low efficiency at low flow rates in multi-stage axial compressors 201, achieving higher flow rates and pressure ratios within a compact size. This invention employs a series-connected combined power scheme, utilizing rotary ram pressurization at low speeds and the ram effect to pressurize the airflow at high speeds. This significantly expands the applicable Mach number range for small turbojet engines, solving the problems of thermal throttling and reduced cycle net power in traditional engines above Mach 3, and substantially increasing engine thrust at high Mach numbers.

[0064] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions 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 rotary ramjet shockwave supercharged gas turbine engine, characterized in that: It includes an outer casing (3) and an inner casing (4), the inner casing (4) being located inside the outer casing (3), and the inner casing (4) and the outer casing (3) forming an outer bypass (304). The outer casing (3) is equipped with guide vanes (301), which are used to guide airflow. The inner casing (4) is equipped with a first mechanism, which is used to pressurize and heat the airflow and perform work. A second mechanism is also provided on one side of the inner casing (4), which is used to pressurize and heat the airflow a second time. The first mechanism includes a rotary ram compressor (402), a first combustion chamber (403), and a second turbine (404); The rotary ram compressor (402) is connected to the second turbine (404); The first combustion chamber (403) is located between the rotary ram compressor (402) and the second turbine (404); The inner casing (4) is also provided with a drain hole (407) on its surface, and the position of the drain hole (407) corresponds to the rotary ram compressor (402). When the aircraft flies below Mach 1.5, the vent (407) is closed, and the pressure is mainly increased by the rotary ram compressor (402). When the aircraft flies at Mach 1.5 to 2, the vent (407) is opened to alleviate the thermal blockage effect of the rotary ram compressor (402). When the aircraft accelerates to Mach 2 or above, the pressure is increased based on the ram action, and the vent (407) is closed at this time. The outer casing (3) is provided with a front section, a middle section and a rear section; The rear section of the guide vane (301) is a binary tail nozzle (303), which is used to adjust the pipe diameter to a first pipe diameter or a second pipe diameter. The rotary ram-shock supercharged gas turbine engine includes a high-speed mode and a low-speed mode; the first pipe diameter is used for the high-speed mode, and the second pipe diameter is used for the low-speed mode. The first pipe diameter is the pipe diameter that first decreases in size along the axial direction of the outer casing (3), and then increases in size again; The second pipe diameter is the pipe diameter that decreases from large to small along the axial direction of the outer casing (3).

2. The rotary ramjet shockwave supercharged gas turbine engine according to claim 1, characterized in that, The guide vane (301) is located at the front opening; The inner casing (4) is located in the front section and on one side of the guide vane (301), while the second mechanism is located in the middle section.

3. The rotary ramjet shockwave supercharged gas turbine engine according to claim 1, characterized in that, The first combustion chamber (403) is also connected to a delivery pipe, which is used to deliver fuel into the first combustion chamber (403).

4. A rotary ramjet shockwave supercharged gas turbine engine according to claim 3, characterized in that, The second mechanism includes a second combustion chamber (406); The second combustion chamber (406) is connected to a conduit (405), which is connected to a delivery pipeline.

5. A rotary ramjet shockwave supercharged gas turbine engine according to claim 1, characterized in that, The inner casing (4) is equipped with several mode switching valves (401) on the side near the guide vane (301), which are used to guide the airflow.

6. A rotary ramjet shockwave supercharged gas turbine engine according to claim 5, characterized in that, The inner wall of the outer casing (3) is equipped with a duct ejector (302), which is used to guide the airflow passing through the outer duct (304) to the second mechanism.

7. A rotary ramjet shockwave supercharged gas turbine engine according to claim 1, characterized in that, The second turbine (404) is connected to a rotary ram compressor (402) via a shaft, and the rotary ram compressor (402) is connected to a guide vane (301) via a shaft.

8. A rotary ramjet shockwave-charged gas turbine engine according to any one of claims 1-7, characterized in that, The outer casing (3) and the inner casing (4) are coaxially arranged.

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