CN109595041B - Variable-circulation large-bypass-ratio turbofan engine - Google Patents
Variable-circulation large-bypass-ratio turbofan engine Download PDFInfo
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- CN109595041B CN109595041B CN201710924605.3A CN201710924605A CN109595041B CN 109595041 B CN109595041 B CN 109595041B CN 201710924605 A CN201710924605 A CN 201710924605A CN 109595041 B CN109595041 B CN 109595041B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
The invention provides a variable-circulation large-bypass-ratio turbofan engine which comprises a plurality of turbine guide vanes, wherein each turbine guide vane comprises a blade part of a fixed structure and a plurality of movable blade segments, and the plurality of movable blade segments are connected through hinges and form a hollow area with the blade part of the fixed structure; and the throat area between the two turbine guide vanes is adjusted by changing the movable blade segments to rotate towards the inside or the outside of the turbine guide vanes. Under the condition of high bypass ratio, the flow area of the turbine guide vane is reduced, the mounting angle of the booster stage guide vane is changed, and the booster stage anti-surge effect can be achieved; energy loss caused by air release after the pressurization stage is avoided, and the full-envelope pressurization stage is realized without air release; the connotation can pass through more air, can provide bigger margin for the development of engine thrust.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a variable-cycle large-bypass-ratio turbofan engine.
Background
FIG. 1 is a schematic structural diagram of a double-shaft direct-drive turbofan engine with a large bypass ratio in the prior art. As shown in fig. 1, a general double-shaft direct-drive turbofan engine with a large bypass ratio sequentially passes through a fan for primarily compressing airflow, a booster stage and a high-pressure compressor for further compressing contained airflow, a combustion chamber for heating the airflow, a high-pressure turbine and a low-pressure turbine for respectively driving the high-pressure compressor and the fan (including the booster stage), and a nozzle for jetting high-temperature and high-pressure airflow at a high speed according to the axial flow direction of the airflow.
In order to improve the propulsion efficiency of the engine, it is effective to divide the air passing through the engine into two paths, one path passing through the compressor, the combustion chamber, the turbine and the tail nozzle of the inner duct, and the other path passing through the bypass fan and the bypass tail nozzle. The ratio of the bypass air flow to the bypass air flow is called bypass ratio.
Within the entire operating envelope, the performance requirements of the aircraft on the engines vary as the operating conditions change. For example, during ground take-off and climb, the thrust requirements of the aircraft on the engine are high. While in cruise mode, the aircraft has a high demand on the fuel consumption of the engine.
At present, in order to solve the above-mentioned requirements, the requirements are generally solved by a variable-bypass-ratio variable-cycle engine design method, namely, during ground takeoff and climb, the engine is operated in a low bypass ratio state, and during economic cruise, the engine is operated in a high bypass ratio state.
A variable cycle engine is an engine whose thermodynamic cycle is varied by changing the geometry, size or position of some of its components. According to the traditional variable-bypass-ratio variable-cycle engine design method, when taking off on the ground, the total temperature of the outlet of a combustion chamber is increased (which is up to 2000-2100K abroad at present), so that the pumping capacity of a core engine is increased, the flow of air flowing through the bypass of the engine is large, and the low-bypass-ratio state is realized. However, the common working line of the pressure stages is greatly reduced, the efficiency of parts is greatly reduced, the through-flow capacity of the pressure stages is limited, the physical flow of the inlet of the high-pressure compressor is not increased enough, and the efficiency of variable circulation is affected. Meanwhile, the temperature of the combustion chamber is high, so that the cooling design and the service life of the hot end part of the engine are greatly influenced. When the economy is patrolled and navigated, reduce core machine suction capacity for the connotation air mass flow reduces, improves engine propulsion efficiency. But simultaneously, the common working line of the booster stages rises, the surge margin of the booster stages is influenced, and particularly, the booster stages are easy to surge in the process of decelerating the engine. Currently, this can only be done by bleeding air at the outlet of the booster stage, however, this approach will sacrifice some of the air compressed by the booster stage, resulting in energy losses.
Therefore, the traditional bypass ratio-variable design enables the front total temperature of the turbine to be high, the booster stage cannot be well matched with the aerodynamic performance of each component, and various advantages brought by the bypass ratio are reduced.
Disclosure of Invention
The invention provides a variable-cycle large-bypass-ratio turbofan engine, which is used for overcoming the defects that in the prior art, the temperature of a combustion chamber outlet is high, the development of thrust margin is limited, the service life of the engine is limited, and meanwhile, the mismatch of booster stage work is caused by variable bypass ratio under the ground take-off and climbing states of the turbofan engine.
The invention solves the technical problems through the following technical scheme:
a variable-cycle high-bypass-ratio turbofan engine comprises a plurality of turbine guide vanes and is characterized in that the turbine guide vanes comprise blade parts of fixed structures and a plurality of movable blade segments, and the movable blade segments are connected through hinges and form a hollow area with the blade parts of the fixed structures; and the throat area between the two turbine guide vanes is adjusted by changing the movable blade segments to rotate towards the inside or the outside of the turbine guide vanes.
According to an embodiment of the present invention, the movable blade segments include a first segment movable blade segment and a second segment movable blade segment, one end of the first segment movable blade segment is connected with one end of the blade portion of the fixed structure by a first hinge, and one end of the second segment movable blade segment is connected with the other end of the blade portion of the fixed structure by a second hinge;
the other end of the first section of movable blade segment and the other end of the second section of movable blade segment are attached to each other.
According to one embodiment of the invention, the turbine guide vane further comprises an adjusting rotating shaft, an adjusting rotating shaft arm, a first transmission arm and a second transmission arm, wherein one end of the first transmission arm is connected with the first section of movable blade segment through a first connecting shaft, and one end of the second transmission arm is connected with the second section of movable blade segment through a second connecting shaft;
the other end of the first transmission arm and the other end of the second transmission arm are connected with the adjusting rotating shaft arm through a third connecting shaft, and the adjusting rotating shaft arm is connected with the adjusting rotating shaft.
According to one embodiment of the invention, the turbine vane has high pressure cooling air inside.
According to one embodiment of the present invention, a blade portion of the fixing structure and the first and second segment movable blade segments have a slit therebetween, and the first and second segment movable blade segments have a slit therebetween.
According to an embodiment of the invention, the movable blade segments comprise a first segment movable blade segment, a second segment movable blade segment and a third segment movable blade segment;
one end of the first section of movable blade segment is connected with one end of the blade part of the fixed structure through a first hinge, the other end of the first section of movable blade segment is connected with one end of the second section of movable blade segment through a second hinge, and the other end of the second section of movable blade segment is connected with one end of the third section of movable blade segment through a third hinge;
the other end of the third section of movable blade segment is connected to the other end of the blade part of the fixed structure through an adjusting rotating shaft.
According to one embodiment of the invention, the turbine vane has high pressure cooling air inside.
According to one embodiment of the invention, the blade portion of the fixed structure and the first and third segments have a gap therebetween, the first and second segments have a gap therebetween, and the second and third segments have a gap therebetween.
According to one embodiment of the invention, the mounting angle of the booster stage guide vane of the variable-circulation high-bypass-ratio turbofan engine is an included angle between a chord line and an axial direction, and the included angle ranges from 0 to 90 degrees.
The positive progress effects of the invention are as follows:
the variable-circulation large-bypass-ratio turbofan engine has the following advantages by changing the flow area of the turbine guide vane and combining the change of the mounting angle of the booster stage adjustable guide vane:
under the condition of high bypass ratio, the flow area of the turbine guide vane is reduced, the mounting angle of the booster stage guide vane is changed, and the booster stage anti-surge effect can be achieved;
energy loss caused by deflation after the pressurization stage is avoided, and the full-envelope pressurization stage is realized without deflation;
thirdly, the pressurization level air release valve and the corresponding adjusting mechanism can be removed structurally;
fourthly, the connotation can pass through more air, and can provide larger margin for the development of the thrust of the engine;
compared with the prior art, the total temperature before the turbine can be reduced under the same thrust condition, and the service life of the engine is prolonged.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings in which like reference numerals denote like features throughout the several views, wherein:
FIG. 1 is a schematic structural diagram of a double-shaft direct-drive turbofan engine with a large bypass ratio in the prior art.
FIG. 2 is a schematic structural diagram of a first embodiment of a turbine vane in a variable-cycle high-bypass-ratio turbofan engine according to the invention.
FIG. 3 is a schematic view showing an arrangement state of a first turbine guide vane in the variable-circulation high-bypass-ratio turbofan engine according to the first embodiment of the invention.
FIG. 4 is a schematic view of a second arrangement state of turbine guide vanes in the variable-circulation high-bypass-ratio turbofan engine according to the first embodiment of the invention.
FIG. 5 is a schematic structural diagram of a second embodiment of a turbine vane in a variable-cycle high-bypass-ratio turbofan engine according to the present invention.
FIG. 6 is a schematic view of a second arrangement of turbine vanes in the variable-cycle high-bypass-ratio turbofan engine according to the first embodiment of the invention.
FIG. 7 is a schematic view of the second layout state of the turbine guide vane in the variable-circulation high-bypass-ratio turbofan engine according to the second embodiment of the invention.
FIG. 8 is a schematic view of a variable cycle high bypass ratio turbofan engine with a boost stage with adjustable vanes of the present invention.
FIG. 9 is a qualitative curve diagram of joint adjustment of a mounting angle of a booster stage and a throat area of a turbine guide vane of the variable-cycle high-bypass-ratio turbofan engine.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
Based on the defects brought by the traditional variable-bypass-ratio design method, the invention realizes a novel variable-circulation large-bypass-ratio turbofan engine by changing the flow area of the turbine guide vane and combining the coordinated operation of the booster stage adjustable guide vane, avoids the defects of the traditional variable-bypass-ratio design method, and specifically comprises a fan, the booster stage of the adjustable guide vane, a high-pressure compressor, a combustion chamber, a turbine with variable geometry guide vanes and a tail nozzle. The variable cycle high bypass ratio turbofan engine of the present invention will be described with reference to the accompanying drawings.
The first embodiment is as follows:
FIG. 1 is a schematic structural diagram of a double-shaft direct-drive turbofan engine with a large bypass ratio in the prior art. FIG. 2 is a schematic structural diagram of a first embodiment of a turbine vane in a variable-cycle high-bypass-ratio turbofan engine according to the invention. FIG. 3 is a schematic view showing an arrangement state of a first turbine guide vane in the variable-circulation high-bypass-ratio turbofan engine according to the first embodiment of the invention. FIG. 4 is a schematic view of a second arrangement state of turbine guide vanes in the variable-circulation high-bypass-ratio turbofan engine according to the first embodiment of the invention.
As shown in fig. 1 to 4, the variable-cycle large-bypass-ratio turbofan engine of the present invention includes a plurality of turbine guide vanes 10 including a fixed-structure blade portion 11, and a plurality of movable blade segments connected by hinges and forming a hollow region with the fixed-structure blade portion 11, and the throat area between two turbine guide vanes 10 is adjusted by changing the movable blade segments to rotate toward the inside or the outside of the turbine guide vanes 10.
Preferably, the movable blade segment in this embodiment includes a first movable blade segment 12 and a second movable blade segment 13, one end of the first movable blade segment 12 is connected with one end of the fixed structure blade portion 11 through a first hinge 14, and one end of the second movable blade segment 13 is connected with the other end of the fixed structure blade portion 11 through a second hinge 15. The other end of the first-stage movable blade segment 12 and the other end of the second-stage movable blade segment 13 are attached to each other.
The turbine guide vane 10 further includes an adjusting rotating shaft 16, an adjusting rotating shaft arm 17, a first transmission arm 18 and a second transmission arm 19, wherein one end of the first transmission arm 18 is connected to the first section of movable blade segment 12 through a first connecting shaft 181, and one end of the second transmission arm 19 is connected to the second section of movable blade segment 13 through a second connecting shaft 191. The other end of the first transmission arm 18 and the other end of the second transmission arm 19 are connected to the adjustment rotation shaft arm 17 through a third connection shaft 182, and the adjustment rotation shaft arm 17 is connected to the adjustment rotation shaft 16.
Further, there is high pressure cooling air inside the turbine vane 10. The blade portion 11 of the fixed structure has a gap between the first-stage movable blade segment 12 and the second-stage movable blade segment 13, and the first-stage movable blade segment 12 and the second-stage movable blade segment 13 have a gap therebetween.
According to the structural description, the working principle of the variable-circulation large-bypass-ratio turbofan engine of the embodiment is as follows: in this embodiment, the blade portion 11 of the fixed structure, the first movable blade segment 12 and the second movable blade segment 13 form a turbine guide vane 10 with a certain hollow structure, and high-pressure cold air is provided inside the turbine guide vane 10 to cool a movable component and a connecting shaft inside the turbine guide vane 10 and connecting hinges of the blades of each portion, so that reliable operation of the turbine guide vane 10 is ensured. Small gaps are formed between the blade portion 11 of the fixed structure and the first and second movable blade segments 12 and 13, and between the first and second movable blade segments 12 and 13. Due to the pressure difference between the internal high-pressure cold air and the external fuel gas, the cold air can form a cooling air film on the outer wall surface of the guide vane through the gap.
Under different working states, the adjusting rotating shaft 16 is rotated through the actuating system to drive the adjusting rotating shaft arm 17, the first transmission arm 18 and the second transmission arm 19 to move, the first transmission arm 18 and the second transmission arm 19 respectively drive the first section of movable blade segment 12, and the second section of movable blade segment 13 rotates towards the inside or the outside of the guide blade around the connecting hinge, so that the throat area between the guide blades is changed, the through-flow capacity of the turbine stage is adjusted, and the through-flow capacity of a culvert flow passage in the engine is improved.
In this embodiment, when the aircraft engine works in a take-off and climbing state, the throat area of the turbine guide vane is enlarged, and the mounting angle of the booster stage guide vane is adjusted to improve the air flow matching of engine parts, so that the flow capacity of the culvert flow passage is increased, and the circulation that the culvert ratio is reduced and the thrust is increased is realized.
Example two:
FIG. 5 is a schematic structural diagram of a second embodiment of a turbine vane in a variable-cycle high-bypass-ratio turbofan engine according to the present invention. FIG. 6 is a schematic view of a second arrangement of turbine vanes in the variable-cycle high-bypass-ratio turbofan engine according to the first embodiment of the invention. FIG. 7 is a schematic view of the second layout state of the turbine guide vane in the variable-circulation high-bypass-ratio turbofan engine according to the second embodiment of the invention.
As shown in fig. 5 to 7, the variable-cycle large-bypass-ratio turbofan engine according to the present invention includes a plurality of turbine guide vanes 20 including a fixed-structure blade portion 21, and a plurality of movable blade segments connected by hinges and forming a hollow region with the fixed-structure blade portion 21, and the throat area between two turbine guide vanes 20 is adjusted by changing the movable blade segments to rotate toward the inside or the outside of the turbine guide vanes 20.
Preferably, the movable blade segment in this embodiment includes a first segment movable blade segment 22, a second segment movable blade segment 23 and a third segment movable blade segment 24. One end of the first movable blade segment 22 is connected to one end of the blade portion 21 of the fixed structure through a first hinge 221, the other end of the first movable blade segment 22 is connected to one end of the second movable blade segment 23 through a second hinge 222, and the other end of the second movable blade segment 23 is connected to one end of the third movable blade segment 24 through a third hinge 231. The other end of the third stage movable blade segment 24 is connected to the other end of the fixed structure blade portion 21 by an adjustment spindle 25. With the above configuration, the blade portion 21, the first-stage movable blade segment 22, the second-stage movable blade segment 23, and the third-stage movable blade segment 24, which are fixed structures, are formed as an integral structure by the first hinge 221, the second hinge 222, and the third hinge 231, which connect the respective blades.
Further, there is high pressure cooling air inside the turbine vane 20. Gaps are formed between the blade portion 21 of the fixed structure and the first and third movable blade segments 22 and 24, gaps are formed between the first and second movable blade segments 22 and 23, and gaps are formed between the second and third movable blade segments 23 and 24.
According to the structural description, the working principle of the variable-circulation large-bypass-ratio turbofan engine of the embodiment is as follows: in this embodiment, the fixed structure blade portion 21, the first movable blade segment 22, the second movable blade segment 23, and the third movable blade segment 24 form a turbine guide vane 20 with a certain hollow center. The turbine guide vane 20 has high-pressure cooling air therein for cooling the movable parts, the connecting shaft and the connecting hinges of the blades in the turbine guide vane, so that reliable operation is ensured. Small gaps are formed between the blade portion 21 of the fixed structure and the first and third movable blade segments 22 and 24, between the first and second movable blade segments 22 and 23, and between the second and third movable blade segments 22 and 24. Due to the pressure difference between the internal high-pressure cold air and the external fuel gas, the cold air can form a cooling air film on the outer wall surface of the guide vane through the gap.
Under different working states, the rotating shaft 25 is adjusted by the rotation of the actuating system to drive the third section of movable blade segment 24 which is designed as a whole to rotate, the third section of movable blade segment 24 drives the connecting hinge to move, and the movement is further transmitted to the second section of movable blade segment 23 and the first section of movable blade segment 22, so that the positions of the second section of movable blade segment 23 and the first section of movable blade segment 22 are changed, and the throat area between the guide blades is changed. The through-flow capacity of the turbine stage is adjusted, the performance matching of components of the turbine under different working conditions is improved, the stability of the engine is improved, and the fuel consumption of the engine is reduced.
FIG. 8 is a schematic view of a variable cycle high bypass ratio turbofan engine with a boost stage with adjustable vanes of the present invention. FIG. 9 is a qualitative curve diagram of joint adjustment of a mounting angle of a booster stage and a throat area of a turbine guide vane of the variable-cycle high-bypass-ratio turbofan engine.
As shown in FIGS. 8 and 9, the variable cycle high bypass ratio turbofan engine of the invention has a booster stage A with adjustable vanes as shown in FIG. 8, and the installation angle thereof can be changed within a certain range. Preferably, the mounting angle of the supercharging stage guide vane of the variable-circulation high-bypass-ratio turbofan engine is an included angle between a chord line and the axial direction, and the included angle ranges from 0 degree to 90 degrees.
When the aviation engine works in an economic cycle state in the embodiment, the throat area of the turbine guide vane is reduced, the mounting angle of the booster stage guide vane is adjusted to improve the air flow matching of engine parts, the through-flow capacity of the inner culvert runner is further reduced, the increase of the bypass ratio is realized, and the propulsion efficiency is improved.
In conclusion, the variable-circulation large-bypass-ratio turbofan engine has the following advantages by changing the flow area of the turbine guide vane and combining the change of the installation angle of the adjustable guide vane of the booster stage:
under the condition of high bypass ratio, the flow area of the turbine guide vane is reduced, the mounting angle of the booster stage guide vane is changed, and the booster stage anti-surge effect can be achieved;
energy loss caused by deflation after the pressurization stage is avoided, and the full-envelope pressurization stage is realized without deflation;
thirdly, the pressurization level air release valve and the corresponding adjusting mechanism can be removed structurally;
fourthly, the connotation can pass through more air, and can provide larger margin for the development of the thrust of the engine;
compared with the prior art, the total temperature before the turbine can be reduced under the same thrust condition, and the service life of the engine is prolonged.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (3)
1. A variable-cycle high-bypass-ratio turbofan engine comprises a plurality of turbine guide vanes and a plurality of supercharging stage guide vanes, and is characterized in that the turbine guide vanes comprise fixed-structure blade parts and a plurality of movable blade segments, and the plurality of movable blade segments are connected through hinges and form a hollow area with the fixed-structure blade parts; adjusting the throat area between two turbine guide vanes by changing the movable blade segments to rotate towards the inside or the outside of the turbine guide vanes;
the movable blade segments comprise a first segment movable blade segment, a second segment movable blade segment and a third segment movable blade segment;
one end of the first section of movable blade segment is connected with one end of the blade part of the fixed structure through a first hinge, the other end of the first section of movable blade segment is connected with one end of the second section of movable blade segment through a second hinge, and the other end of the second section of movable blade segment is connected with one end of the third section of movable blade segment through a third hinge;
the other end of the third section of movable blade segment is connected to the other end of the blade part of the fixed structure through an adjusting rotating shaft;
the mounting angle of the supercharging stage guide vane of the variable-circulation large-bypass-ratio turbofan engine is an included angle between a chord line and the axial direction, and the included angle ranges from 0 degree to 90 degrees.
2. The variable cycle high bypass ratio turbofan engine of claim 1 wherein the turbine vanes have high pressure cooling air therein.
3. The variable cycle large bypass ratio turbofan engine of claim 1 wherein gaps are provided between the blade portion of the stationary structure and the first and third sections of movable blade segments, wherein gaps are provided between the first and second sections of movable blade segments, and wherein gaps are provided between the second and third sections of movable blade segments.
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| US20210108572A1 (en) * | 2019-10-15 | 2021-04-15 | General Electric Company | Advance ratio for single unducted rotor engine |
| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113062777B (en) * | 2021-06-03 | 2021-10-01 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
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