CN112814949B - Oblique-section type double-freedom-degree inlet adjustable guide vane suitable for wide bypass ratio variation range - Google Patents
Oblique-section type double-freedom-degree inlet adjustable guide vane suitable for wide bypass ratio variation range Download PDFInfo
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- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
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- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
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Abstract
The invention provides a truncated double-freedom-degree inlet adjustable guide vane suitable for a wide bypass ratio variation range, and relates to an adjustable guide vane technology for realizing partition control by changing a blade profile based on double freedom degrees in a full three-dimensional mode. The two-degree-of-freedom inlet adjustable guide vane suitable for the wide bypass ratio variation range is based on a common adjustable guide vane design technology, inherits the advantages, increases the adjustable dimensionality of the blades, is suitable for a self-adaptive variable circulation fan, and can ensure the efficiency ratio of the fan so that the fan can normally work under all working conditions. The variable-geometry adjustable inlet guide vane with two degrees of freedom is designed by changing the geometry of a vane profile on the basis of the traditional adjustable inlet guide vane suitable for a common turbofan engine, can perform prewhirl adjustment on the air inlet of a downstream rotor impeller, can adjust the prewhirl degree of different vane height positions simultaneously, improves the quality of outlet airflow, solves the problem that the position of the vane height of a fan facing surge risk under different bypass ratio working conditions is changed, and has very obvious gain for improving a self-adaptive variable-cycle engine.
Description
Technical Field
The invention provides a truncated double-freedom-degree inlet adjustable guide vane suitable for a wide bypass ratio variation range, and belongs to the technical field of aviation power devices.
Background
With the development of science and technology, the requirement on the comprehensive combat capability of the advanced fighter is more and more severe, the engine is used as the heart of the fighter and is a decisive factor for determining the performance of the fighter, and the cross-era development of the fighter every time can not leave the updating and updating of the engine design technology. According to the analysis of the operation requirements of the future fighter, the next generation fighter has the technical characteristics of 'supersonic cruise, unconventional maneuver, ultra-long range strike' and the like. Engines relying on fixed cycles have not been able to meet the operational performance requirements of advanced fighters.
The traditional turbojet engine has high unit thrust under supersonic speed conditions, and the turbofan engine has lower oil consumption rate when flying at subsonic speed. In order to integrate two advantages of high unit thrust and low fuel consumption rate to obtain the optimal comprehensive performance in the whole flight envelope, the concept of a variable cycle engine is firstly proposed in the last 60 th century in the United states, and the aim is to combine the advantages of low fuel consumption of a large bypass ratio turbofan under the subsonic flight condition and high thrust of a small bypass ratio turbofan under the supersonic speed condition, so that the multitask performance requirement of an aircraft is met. The existing research shows that in a wider flight Mach number range, the variable-cycle engine can almost accommodate all the flow captured by the air inlet channel through stronger inlet flow retaining capacity, reduce the installation resistance of the engine, increase the thrust of the engine and simultaneously reduce the fuel consumption rate of the engine.
The self-adaptive engine is additionally provided with the adjustable third duct on the basis of the core engine and the low-pressure compression system of the double-bypass variable-cycle engine, so that thermodynamic cycle parameter optimization in a wider range can be realized, the requirement of the future engine on variable cycle is met, and the comprehensive performance of the aircraft is improved to a greater extent. At present, the united states is leading in the foreign research on the adaptive variable cycle engine, and the research on the adaptive variable cycle engine (mainly an adaptive engine with an adaptive fan as a key structure) mainly comprises the following plans:
1.ADVENT
in 2007, the United states initiated the adaptive Universal Engine technology program (ADVENT) that developed and validated the adaptive cycle engine, the goal of the ADVENT program was to develop technologies that could independently vary the fan/core airflow and pressure ratios, and the GE company developed and validated the FLADE fan adaptive engine in the ADVENT program. Through comprehensive tests on the three-bypass engine and the adaptive fan, the ADVENT engine of GE company meets all performance and durability indexes.
2.AETD
The adaptive engine technology development project (AETD) is a follow-up project of the ADVENT project, and aims to promote the maturity of the three-foreign adaptive engine technology and provide power meeting the technical requirements for the next generation of American air force fighters in the coming years. Compared with an F135 engine, the fuel consumption of the adaptive engine developed and verified by the plan can be reduced by 20%, the net thrust can be increased by 5%, the boosting thrust can be increased by 10%, the range can be extended by 30%, and the adaptive engine can be used as the power of an F-35 fighter through subsequent improvement. The PW company performs a bench test of the adaptive fan in 2013, and performs an engine test of a stress application and exhaust system of the core machine and the adaptive fan in the first half of 2016.
3.AETP
The AETP program is a successor to the AETD research program, yet another technical maturity program for adaptive engines. The project was initiated at 2016 and 6 months, and the GE and PW were responsible for the technical development and validation of the adaptive engine.
The self-adaptive fan is a key part of the self-adaptive variable-cycle engine, and is used for completing the special functions of the self-adaptive variable-cycle engine such as flow regulation, variable bypass ratio and the like besides the traditional fan supercharging effect, realizing good matching of multiple working points, stably running in the working mode switching process and strongly coupling with the whole self-adaptive variable-cycle engine. The performance requirement of the self-adaptive fan is severe, and the traditional imported adjustable guide vane is singly relied on to be difficult to meet the new performance requirement, so the research and development design of the novel imported adjustable guide vane suitable for the self-adaptive fan is a key technology for ensuring the stable work of the self-adaptive fan and realizing the multi-performance requirement.
Disclosure of Invention
The invention provides a truncated two-degree-of-freedom inlet adjustable guide vane adaptive to a wide bypass ratio change range, relates to an adjustable guide vane technology for realizing partition control by changing a blade profile based on two degrees of freedom in a full three-dimensional mode, can be used for an adaptive variable-cycle turbofan engine, and aims to improve the adjustable guide vane technology of a traditional engine and enable the adjustable guide vane technology to be applicable to the adaptive variable-cycle engine, so that a first-stage adaptive fan of the adjustable guide vane technology has the characteristics of high working efficiency (the whole working condition of the fan is maintained at a design point), strong compression capability, wide stability margin (a transition state between mode switching can maintain higher efficiency and still has strong compression capability) and the like. The invention is based on the common adjustable guide vane design technology, inherits the advantages, increases the adjustable dimension of the blades, is suitable for the self-adaptive variable circulation fan, and can ensure the efficiency ratio of the fan to ensure the normal work of the fan in all working conditions.
The technical solution of the invention is as follows:
in a maximum bypass ratio design state under a fixed flow, the inlet guide vane maintains the initial blade profile without variable geometric actuation or small amplitude adjustment, the fan decelerates and pressurizes the airflow, the airflow flows smoothly, and the problems of flow separation and the like are almost avoided; along with the reduction of the bypass ratio, the flow of the bypass is gradually reduced, the inlet attack angle of the blade tip part of the fan is sharply increased due to the reduction of the flow, the flow separation phenomenon occurs, at the moment, the blade tip is reduced by the rotation angle of the inlet adjustable guide blade, the large attack angle of the blade tip due to the reduction of the flow is ensured, the working stability of the fan is ensured, and meanwhile, the blade root and the blade leaf of the inlet guide blade are also required to be controlled to adjust the angles so as to maintain the supercharging capacity of the rest parts of the fan except the blade tip.
The adjustable stator of oblique section formula two degree of freedom import of adaptation wide bypass ratio variation range, its structure includes: a main blade 1, a secondary blade 2 and a connecting mechanism 3. The main blade 1 and the auxiliary blade 2 are hinged through a connecting mechanism 3. The guide vane is provided with a two-stage adjusting rotating shaft, the main shaft A is positioned at the top of the main blade 1, and the main shaft is rotated to control the adjusting angle of the main blade 1 and the auxiliary blade 2; the auxiliary shaft B is positioned at the top of the auxiliary blade 2 and controls the hinge to rotate so as to adjust the rotation angle of the auxiliary blade 2.
On the basis of the determined initial blade profile, selecting an auxiliary blade area, wherein the specific method comprises the following steps: firstly, determining the lowest blade height position of a flow separation group in a fan flow field in the full-bypass-ratio working range, and taking the lowest blade height position as the end points of an auxiliary blade and a main blade of an inlet adjustable guide blade on the trailing edge line of a blade profile; evaluating the influence degree of a coupling mechanism formed by the self-adaptive fan blade tip separation group and the blade tip leakage on a flow field under the working condition of the minimum bypass ratio, reasonably distributing the proportion of the main blade and the auxiliary blade at the blade top of the inlet adjustable guide blade to the blade top molded surface respectively according to the evaluation result, and finally connecting two intersection points of the rear edge line and the blade top of the inlet adjustable guide blade, wherein the initial blade type of the inlet adjustable guide blade is divided into two parts, and the part with smaller volume is the auxiliary blade 2.
The two-degree-of-freedom geometrically adjustable guide vane adjusting mechanism comprises:
1) maximum bypass ratio state: the adjustable guide vane keeps an initial profile, and the main blade 1 is adjusted in a small range through the main shaft A according to the existence of a separation group in a flow field in the fan blade, so that the influence of the separation group on the flow is eliminated, and the quality of the air flow supplied to the core machine is ensured;
2) minimum bypass ratio state: the fan blade tip has a strong separation group and is coupled with the blade tip leakage, the angle of the auxiliary shaft B is adjusted to apply positive prerotation, and the problem of the increase of the attack angle of inlet airflow caused by throttling is reduced so as to adapt to the flow of the fan blade tip;
3) and in the flight state between the maximum bypass ratio and the minimum bypass ratio, the two rotating shafts are cooperatively adjusted according to the actual condition of the fan flow field, so that the aim of optimal control is fulfilled.
The invention has the beneficial effects that: the self-adaptive variable-cycle fan has the advantages that the advantages of the traditional inlet adjustable guide vanes are inherited, meanwhile, the self-adaptive variable-cycle fan can be guaranteed to be maintained at high performance within the full working condition range, the quality of outlet airflow is improved, and the self-adaptive variable-cycle fan has remarkable gains in improving the fighting capacity of the self-adaptive variable-cycle engine. The self-adaptive fan has obvious performance advantages in a full-bypass ratio range, the compression efficiency of the self-adaptive fan is obviously improved, and the flow condition is good.
Drawings
FIG. 1 is a schematic diagram of a three-dimensional structure of a two-degree-of-freedom inlet adjustable guide vane.
FIG. 2 is a longitudinal sectional view of a two degree of freedom inlet adjustable vane.
FIG. 3 is a schematic view of the articulation of the primary and secondary vanes.
FIG. 4 is a graphical representation of the relationship between fan blade inlet angle parameters and velocity triangles.
FIG. 5 is a schematic diagram of the distribution of fan separation zones under the working conditions of large bypass ratio and small bypass ratio.
FIG. 6 is a schematic view showing the change of the profile of the main shaft by adjusting the rotation angle of the small blade and the large blade.
FIG. 7 is a schematic view showing the change of the profile of the large blade height section for adjusting the rotation angle of the auxiliary shaft.
FIG. 8 is a schematic diagram of the profile variation of the large blade height section for adjusting the main shaft and the auxiliary shaft simultaneously.
In the attached drawings, 1 is a main blade, 2 is an auxiliary blade, and 3 is a connecting mechanism; a is a main shaft and B is an auxiliary shaft; p represents the rotation center of the front edge of the blade, and Q1 and Q2 represent the hinge point of the main blade and the auxiliary blade, namely the rotation center of the auxiliary blade; and a and b respectively represent the air flow tracks under two adjusting angles.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings.
The invention is a fan inlet basic angle parameter and velocity triangle according to figure 4, wherein the angle of attack
When the large airflow with excessive attack angle enters the fan, the airflow does not flow around the blades and is separated from the surfaces of the blades to form a separation area, and the air inlet angle can be increased by applying positive prerotation
Thereby reducing the angle of attack
The separation area is reduced or even eliminated, thereby realizing widening of the fan surge boundary. The airflow flow conditions are improved by applying different degrees of inlet pre-swirl, which is the fundamental theory in the design of inlet adjustable guide vanes. On the basis of the original profile of the inlet adjustable guide vane adjusted by a single degree of freedom, an inclined adjustable auxiliary shaft B is added, the vane is divided into a main vane 1 and an auxiliary vane 2 along the auxiliary shaft B, and a connecting mechanism 3 between the main vane 1 and the auxiliary vane 2 is simultaneously used as an auxiliary shaft adjusting mechanism.
According to the variable geometry adjusting scheme of the two-degree-of-freedom adjustable inlet guide vane, the high flow field of the self-adaptive fan small vane hardly has serious flow problems in the full-bypass ratio range, and great influence on the airflow flow of the flow field is not caused when the inlet guide vane is adjusted, so that the three-dimensional non-bending twisted blade with the non-bending symmetrical blade profile as the section blade profile is used as the initial three-dimensional blade profile for variable geometry adjustment of the inlet guide vane. Different from a common inlet adjustable guide vane, the guide vane of an initial three-dimensional blade profile is divided into a main blade 1 and an auxiliary blade 2 in an inclined section mode according to the fan flow field analysis function requirement, and the two parts are connected through a plurality of pairs of hinges. With the change of working conditions, the local flow structure of the downstream fan flow field is changed, the two-stage rotating shaft is adjusted according to the flow field change rule, and the guide vane can control the fan flow field in two degrees of freedom.
Considering that the inlet adjustable guide vane only plays a role in rectification and is small in pneumatic load, the whole guide vane adopts a hollow vane design so as to facilitate subsequent installation of a connecting mechanism and simultaneously reduce the weight of the whole inlet adjustable guide vane.
Comparing with the attached figures 1 and 3, the truncated two-freedom-degree inlet adjustable guide vane suitable for the wide bypass ratio variation range structurally comprises: main blade 1, auxiliary blade 2, coupling mechanism 3 and two-stage regulation pivot.
The two-stage adjusting rotating shaft comprises a main shaft A and an auxiliary shaft B, the main shaft A is positioned at the top of the main blade 1, and the main shaft A can be rotated to control the adjusting angle of the main blade 1 and the auxiliary blade 2; the auxiliary shaft B is positioned at the top of the auxiliary blade 2, and the rotation of the connecting mechanism 3 is controlled to adjust the rotation angle of the auxiliary blade 2. In order to prevent the two-stage adjusting rotating shaft from generating mechanical interference, the position of the main shaft A is close to the front edge of the main blade 1 and is positioned in the range of 10% -30% of the chord length of the blade, and the perpendicular line of the center of the leaf profile inscribed circle at the position is the main shaft A; the vertex of the auxiliary shaft B is close to the midpoint of the camber line of the blade profile at the blade top and is positioned in the range of 45% -50% of the chord length of the blade, and the intersection line of the auxiliary shaft B and the main blade and the auxiliary blade is parallel, particularly referring to the attached figure 2.
Determining the adjusting angle of the two-stage adjusting rotating shaft: the main blade 1 can control a whole-blade high flow field, the flow field at the bottom of the fan blade does not need to be controlled, and in order to prevent excessive interference on the flow field at the bottom of the blade, the main shaft A takes an initial blade-shaped mean camber line as a reference, and the adjusting range of rotation around a rotating shaft is +/-20 degrees; the auxiliary shaft B has no influence on a flow field at the bottom of the fan, and simultaneously needs to adapt to complex coupling flow of the top of the fan blade, and needs stronger prerotation capacity than the main shaft A, and the auxiliary shaft B takes the initial blade profile as a reference, and the adjustment range of rotation around the rotating shaft is +/-30 degrees.
FIG. 4 is a diagram showing the flow separation reason of the fan and the principle of the inlet guide vane application control, and FIG. 5 is a diagram showing the separation region distribution diagram of the downstream fan in the state of large bypass ratio and the separation region distribution diagram in the state of small bypass ratio. The L point is the lowest height of the separation region in a large bypass ratio state, the height corresponding to the L point is used as the height of the intersection point of the main blade 1 and the auxiliary blade 2 at the rear edge of the guide vane, and a truncated end point is determined; the S point corresponds to the blade tip, the separation area is the largest, the maximum control strength is required, the longer the length of the auxiliary blade is, the stronger the capability of controlling the airflow direction is, the intersection point of the main blade 1 and the auxiliary blade 2, which are positioned at the top of the guide blade, is selected to be close to the front edge of the guide blade and is positioned at 35% -45% of the chord length, the top point of the truncated form is determined, and the division and connection relation of the blades is determined.
Fig. 6-8 show the actuation of two-stage adjusting shafts under different working conditions: referring to fig. 6, in the maximum bypass ratio state, the fan blade has a small-range separation area, the required control strength is not large, the rotation angle of the main shaft is adjusted to apply positive prerotation to the fan, and small and medium separation clusters in the fan blade are eliminated; referring to fig. 7, in a minimum bypass ratio state, the blade root flows smoothly, the blade tip has a large separation area, the auxiliary shaft is adjusted to deflect the auxiliary blade, and the airflow of the blade tip is applied with 'forward prerotation' to adapt to the problem of 'large attack angle' of the blade tip of the fan caused by flow reduction; referring to the attached figure 8, in the intermediate bypass ratio state, the 'attack angle' of the fan airflow changes along the blade height, the separation group gradually migrates to the top of the fan blade along with the reduction of the bypass ratio, the flow below the blade tends to be smooth, and the excessive adjustment of the main shaft is unfavorable for the flow field below the blade, so that the intermediate state adjustment follows the principle that the auxiliary shaft is used as a main shaft and the main shaft is used as an auxiliary shaft, the two-stage rotating shafts are adjusted in a coordinated manner, and the positive prerotation of different degrees is applied to different blade heights.
Example 1
Aiming at the variable circulation fan with a certain bypass ratio of 0.05-0.9 working range, the performance requirements are that the fan efficiency is not lower than 87% under any bypass ratio, the pressure increasing ratio is not lower than 1.8, and the stability margin reduction value is not higher than 9%. In a 0.9 bypass ratio state (turbofan engine mode), the fan flow distribution is uniform, small-range flow separation exists only in the blades, the rotating shaft A is adjusted in a small range to eliminate separation clusters in the blades to improve the flow condition of the fan, the bypass ratio is gradually reduced, the separation clusters gradually move towards the blade tip part, two rotating shafts are reasonably adjusted according to the positions of the separation clusters (only the rotating shaft A is adjusted, only the rotating shaft B is adjusted or two shafts are matched in a cooperative mode), and the influence of guide vane angle adjustment on the high flow of the rest blades of the fan is reduced while the separation clusters are weakened. In the state of a bypass ratio of 0.05 (in a turbojet engine mode), due to the fact that the bypass is greatly throttled, the fan blade tip generates a separation mass and is coupled with the blade tip leakage, the auxiliary shaft B is reasonably adjusted according to the flowing condition, and the adjusting angle capable of improving the blade tip flow field is determined. In a 0.05-0.9 bypass ratio mode, two shafts are adjusted in a coordinated mode, the efficiency of the fan is maintained at 88.3% -90.6%, the boosting ratio is up to 1.89-1.97, and the reduction value of the stability margin is less than 6.4%.
The ranges of the operating duct ratio and mach number of the adaptive fan are not defined above, but are merely preferred embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can substitute or change the technical solution and the inventive concept of the present invention within the technical scope of the present invention, and shall be covered by the scope of the present invention.
Claims (8)
1. The adjustable guide vane of truncated two-degree-of-freedom inlet adapting to wide bypass ratio variation range is characterized by comprising the following structures: the device comprises a main blade (1), an auxiliary blade (2), a connecting mechanism (3) and a two-stage adjusting rotating shaft; the guide vane of the variable geometry adjustment initial three-dimensional blade profile is divided into a main blade (1) and an auxiliary blade (2) in a truncated mode and is hinged through a connecting mechanism (3); the top of the guide vane is provided with a two-stage adjusting rotating shaft which is a main shaft (A) and an auxiliary shaft (B) respectively; the main shaft (A) is positioned at the blade top of the main blade (1), and the main shaft is rotated to control the adjusting angle of the main blade (1) and the auxiliary blade (2); the auxiliary shaft (B) is positioned at the top of the auxiliary blade (2), controls the connecting mechanism (3) to rotate and adjusts the rotating angle of the auxiliary blade (2);
the truncated type dividing guide vane comprises a determined vertex and an end point, and the vertex and the end point are connected to divide the main blade and the auxiliary blade: according to the influence degree of a coupling mechanism formed by the separation mass of the blade tip and the blade tip leakage of the self-adaptive fan under the working condition of the minimum bypass ratio on a flow field, determining that the vertex is close to the front edge of the guide blade and is positioned at the position of 35% -45% of the chord length; the end point is positioned at the trailing edge of the blade, and the height of the end point is the lowest blade height position of a flow separation group in a fan flow field in the full-bypass ratio working range;
the two-stage rotating shaft adjusting method comprises the following steps:
1) maximum bypass ratio state: the fan blade is provided with a small-range separation area, the required control strength is not large, the rotation angle of the main shaft is adjusted to apply positive prerotation to the fan, and small separation clusters in the fan blade are eliminated;
2) minimum bypass ratio state: the blade root flows smoothly, the blade tip has a large separation area, the auxiliary shaft is adjusted to deflect the auxiliary blade, and the 'forward prerotation' is applied to the airflow of the blade tip to adapt to the 'large attack angle' problem of the blade tip of the fan caused by the reduction of the flow;
3) intermediate bypass ratio state: the 'attack angle' of fan airflow changes along the blade height, the separation group gradually migrates to the top of the fan blade along with the decrease of the bypass ratio, the flow below the blade tends to be smooth, the two-stage rotating shaft is adjusted in a coordinated mode according to the principle that the auxiliary shaft is used as the main shaft and the main shaft is used as the auxiliary shaft, and the 'positive prerotation' with different degrees is applied to different blade heights.
2. The truncated two-degree-of-freedom inlet adjustable guide vane according to claim 1, wherein the variable geometry initial three-dimensional profile is a three-dimensional non-twisted blade with a non-bent symmetrical profile as a cross-sectional profile.
3. The truncated two-degree-of-freedom inlet adjustable guide vane according to claim 1 adapted to a wide bypass ratio variation range is characterized in that the whole guide vane is designed with hollow blades.
4. The truncated two-degree-of-freedom inlet adjustable guide vane adapting to the wide bypass ratio variation range according to claim 1, characterized in that the connecting mechanism (3) is a plurality of pairs of hinges.
5. The truncated two-degree-of-freedom inlet adjustable guide vane adapting to the wide bypass ratio variation range according to claim 1, characterized in that the main shaft (A) is positioned at the top of the main blade (1) and close to the front edge of the main blade (1), and the main shaft (A) is perpendicular to the center of a leaf-shaped inscribed circle at the position of 10% -30% of the chord length of the blade.
6. The truncated two-degree-of-freedom inlet adjustable guide vane according to claim 5, characterized in that the main shaft (A) is rotated around the rotation axis within a range of ± 20 ° with reference to the initial profile mean camber line.
7. The truncated two-degree-of-freedom inlet adjustable guide vane adapting to the wide bypass ratio variation range according to claim 1 is characterized in that the auxiliary shaft (B) is positioned at the top of the auxiliary blade (2) and is parallel to the intersection line of the main blade (1) and the auxiliary blade (2); the vertex of the auxiliary shaft (B) is close to the midpoint of the camber line of the blade profile at the blade top and is positioned behind 45 percent of chord length of the blade.
8. The truncated two-degree-of-freedom inlet adjustable guide vane according to claim 7, characterized in that the secondary shaft (B) is rotated around the axis of rotation within ± 30 ° with reference to the initial profile.
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| CN113982994B (en) * | 2021-10-28 | 2024-05-28 | 西安热工研究院有限公司 | Novel capacity-increasing transformation method for movable blade adjustable axial flow fan of power station |
| CN114876694B (en) * | 2022-06-10 | 2024-03-01 | 西安理工大学 | Actively-controllable double-movable guide vane device suitable for mixed-flow water turbine |
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| CN105715574A (en) * | 2014-12-05 | 2016-06-29 | 上海电气集团股份有限公司 | Vane regulation control device |
| CN104595245A (en) * | 2015-01-04 | 2015-05-06 | 南京航空航天大学 | Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof |
| CN105332952A (en) * | 2015-11-02 | 2016-02-17 | 南京航空航天大学 | Small-bend adjustable stator design method |
| CN107725482A (en) * | 2016-08-10 | 2018-02-23 | 上海电气燃气轮机有限公司 | Improve the sectional-regulated exit guide blade and its governor motion of compressor off design performance |
| CN111102098A (en) * | 2020-01-03 | 2020-05-05 | 中国科学院工程热物理研究所 | Turbojet propulsion system based on front-mounted compression guide impeller and control method |
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