CN110645052B - Turbine of aircraft engine - Google Patents
Turbine of aircraft engine Download PDFInfo
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- CN110645052B CN110645052B CN201911019930.0A CN201911019930A CN110645052B CN 110645052 B CN110645052 B CN 110645052B CN 201911019930 A CN201911019930 A CN 201911019930A CN 110645052 B CN110645052 B CN 110645052B
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- fan blade
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- rotating rod
- blade group
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- 244000309464 bull Species 0.000 claims description 41
- 238000007664 blowing Methods 0.000 claims description 23
- 241000883990 Flabellum Species 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 238000001816 cooling Methods 0.000 abstract description 13
- 230000000694 effects Effects 0.000 abstract description 9
- 239000007789 gas Substances 0.000 description 61
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of aviation turbines, and particularly relates to an aviation engine turbine which comprises an outer cover, turbine fan blades, a rotating rod and an auxiliary fan blade group, wherein the rotating rod is rotatably arranged in the outer cover; the front end of the rotating rod is fixedly provided with a turbine fan blade, and the outer surface of the middle part of the rotating rod is fixedly provided with an auxiliary fan blade group; the diameter of the turbine fan blade is larger than that of the auxiliary fan blade group; the auxiliary fan blade group is arranged in a symmetrical shape at two ends, and the diameter of the fan blade of the auxiliary fan blade group is arranged from small to large from the inner end to the outer end; the invention mainly aims to solve the problems that in the prior art, when a rotatable turbine blade in a turbine engine works, higher temperature is generated, so that a rotating shaft is blocked due to high-temperature expansion, and meanwhile, a cold air channel is difficult to arrange on the rotating shaft, so that cold air cannot be provided for the inside of the rotating shaft to bring a cooling effect.
Description
Technical Field
The invention belongs to the technical field of aviation turbines, and particularly relates to an aviation engine turbine.
Background
A turbo engine (turbo engine, or turbo for short) is an engine type that uses a rotating member to draw kinetic energy from a fluid passing through the engine, and is one of internal combustion engines, and is commonly used as an engine for an airplane, a large-sized ship or a large-sized vehicle. The variable geometry turbine guide vane is adopted, so that the common working relation of a compression part and a turbine part of the engine can be changed, the gas compressor and the turbine work in a better state, or the gas compressor is ensured to have enough stability margin; moreover, for the double-rotor turbine engine, the rotating speed difference of the high-pressure rotor and the low-pressure rotor can be changed by changing the flow area of the guide vane of the low-pressure turbine, so that the variable cycle function is realized, the efficiency of the engine is improved, and the working range of the engine is expanded, so that the working performance of the engine can be improved and the working range of the engine can be expanded by the variable geometry turbine guide vane.
In order to change the flow area of the turbine guide vane, the rotatable guide vane is generally adopted in the prior art, and the installation angle of the blade is changed by rotating the turbine guide vane so as to change the flow area of the turbine guide vane. However, this method has several problems in the following respects:
(1) the sealing system of the rotatable guide vane is complex and difficult to cool, once the cooling is not good, the problem of jamming between rotating shafts due to high-temperature expansion is caused, and the working reliability is low;
(2) the turbine guide vane works in high-temperature combustion gas, generally needs to be cooled by cold air, the blade of the rotatable guide vane is separated from the upper edge plate and the lower edge plate, the blade is only connected with the upper edge plate and the lower edge plate through the rotating shaft, the rotating shaft is generally thin, the cold air is difficult to be provided for the inside of the turbine guide vane in a mode of arranging a cold air channel on the rotating shaft, great difficulty is brought to the cooling of the turbine guide vane, and therefore the cooling problem cannot be well considered in the prior art.
Disclosure of Invention
In order to make up for the defects of the prior art, the invention provides an aircraft engine turbine. The invention is mainly used for solving the problems that in the prior art, when a rotatable turbine blade in a turbine engine works, higher temperature is generated, so that a rotating shaft is blocked due to high-temperature expansion, and meanwhile, a cold air channel is difficult to arrange on the rotating shaft, so that the cold air cannot be provided for the inside of the rotating shaft to bring a cooling effect.
The technical scheme adopted by the invention for solving the technical problems is as follows: the invention relates to an aircraft engine turbine, which comprises an outer cover, turbine fan blades, a rotating rod and an auxiliary fan blade group, wherein the rotating rod is rotatably arranged in the outer cover; the front end of the rotating rod is fixedly provided with turbine fan blades, and the outer surface of the middle part of the rotating rod is fixedly provided with an auxiliary fan blade group; the diameter of the turbine fan blade is larger than that of the auxiliary fan blade group; the auxiliary fan blade group is symmetrically arranged at two ends, and the diameter of the fan blade of the auxiliary fan blade group is set from small to large from the inner end to the outer end; when the engine turbine starts to operate, the diameter of the turbine fan blade is larger than that of the auxiliary fan blade group, so that the turbine fan blade can pump air to the inner wall of the outer cover when the engine turbine starts to operate, and in the rotating process of the turbine fan blade, the auxiliary fan blade group exists, so that the air pumped by the turbine fan blade can be sucked by the auxiliary fan blade group to be divided into a part, flows along the inner side of the outer cover, and the auxiliary fan blade group is symmetrically arranged at two ends, and the diameter of the fan blade of the auxiliary fan blade group is set from small to large from the inner end to the outer end, so that the air flow pumped by the turbine fan blade can be uniformly divided, the acting force of the air flow on the inner wall of the outer cover is reduced, namely, the temperature in the outer cover is reduced, and the phenomenon that the rotating rod is rapidly heated due to overhigh temperature in the outer cover is avoided.
The middle part of the rotating rod is fixedly provided with a gas gathering box; the air gathering box is annular, is arranged in the middle of the auxiliary fan blade group, and is provided with an opening at the front end and an air inlet inside; the air inlet is formed in the middle wall of the rotating rod; the interior of the rotating rod is hollow, and air leakage holes are uniformly formed in the right end wall of the rotating rod; the air leakage hole is arranged in a circular shape; when engine work drove turbine flabellum and supplementary flabellum group and rotates, have the gas box of gathering because of the middle part fixed mounting of bull stick, gather the gas box and establish the positive middle part at supplementary flabellum group, the front end of gathering the gas box is provided with the opening, so engine during operation has partly air current to enter into through the opening that gathers gas box front end and gather in the gas box, the air inlet has been seted up because of gathering the inside of gas box again, the air inlet is seted up in the middle part wall of bull stick, can enter into the bull stick through the air inlet when the air current enters into gathering the gas box promptly, and finally carry away through the disappointing hole of bull stick right-hand member, realize the cooling processing to the bull stick, avoid the bull stick to be in high temperature state for a long time and take place thermal expansion and cause the deformation to cause the incident.
A power rod is rotatably arranged in the rotating rod through a bearing; the middle part of the power rod is fixedly provided with a gas gathering fan; the air gathering fan is arranged around the power rod in a concave shape, and the outer end of the air gathering fan is arranged at the air inlet; when the air current circulates in the bull stick inside, install the power pole because of the inside of bull stick rotates through the bearing, the middle part fixed mounting of power pole has the gas fan of gathering, and gathers the gas fan and be the spill setting around the power pole, gathers the outer end setting of gas fan in air inlet department, so the air current can drive when entering into the bull stick inside through the air inlet and gathers the gas fan and rotate to pour the air current that passes through into fast into the bull stick, thereby further improve the radiating efficiency to the bull stick.
The inner wall of the gas gathering box is fixedly connected with a blast ring; the middle part of the air blowing ring is arranged in a convex arc shape, and two ends of the air blowing ring are fixedly connected to the inner wall bulges of the air gathering box; when the air current is in through gathering the gas box in, because of gathering the inner wall fixedly connected with air ring of gas box, the middle part of air ring is convex arc setting, and the both ends fixed connection of air ring is on gathering the inner wall arch of gas box, so the air current gets into and gathers the air inlet department that can be got into the bull stick by furthest because of the existence of air ring when gas box, has increased substantially promptly and has gathered the rotational speed of gas fan to further improve the cooling effect to the bull stick.
The inner wall of the air blowing ring is provided with a spiral groove; when gathering the gas box at the during operation, seted up the helicla flute because of the inner wall of air ring, so the air current can be the air inlet department on the heliciform entering bull stick because of the effort that receives helicla flute on the air ring when entering into gathering the gas box, has improved the effort of air current promptly by a wide margin, thereby has improved promptly and has gathered the effort of gas fan rotational speed to make to gather the cooling effect of gas fan rotational speed improvement to the bull stick.
The air blowing ring is made of rubber materials, and an expansion bag is fixedly connected inside the air blowing ring; the expansion bag is arranged in a ring shape, and the outer end of the expansion bag is fixedly connected to the inner wall of the periphery of the gas gathering box; when the blast air ring is at the during operation, because of the blast air ring is made by rubber materials, the inside fixedly connected with inflation bag of blast air ring, the inflation bag sets up to the annular, the outer end fixed connection of inflation bag is on gathering the inner wall all around of gas box, so the blast air ring can be interrupted when receiving the extrusion of air current and sunken to the inner end, extrude the inflation bag promptly, even make the blast air ring send into wind-force to the air inlet in the twinkling of an eye because of the reset action of inflation bag when the effort reduces, ensure promptly to gather the gas fan and be in high-speed running state always, ensure the drainage effect to the air, thereby reach the high-efficient radiating action to the bull stick.
The invention has the following beneficial effects:
1. when the engine turbine starts to operate, the diameter of the turbine fan blade is larger than that of the auxiliary fan blade group, so that the turbine fan blade can pump air to the inner wall of the outer cover when the engine turbine starts to operate, and in the rotating process of the turbine fan blade, the auxiliary fan blade group exists, so that the air pumped by the turbine fan blade can be sucked by the auxiliary fan blade group to be divided into a part, flows along the inner side of the outer cover, and the auxiliary fan blade group is symmetrically arranged at two ends, and the diameter of the fan blade of the auxiliary fan blade group is set from small to large from the inner end to the outer end, so that the air flow pumped by the turbine fan blade can be uniformly divided, the acting force of the air flow on the inner wall of the outer cover is reduced, namely, the temperature in the outer cover is reduced, and the phenomenon that the rotating rod is rapidly heated due to overhigh temperature in the outer cover is avoided.
2. When engine work drove turbine flabellum and supplementary flabellum group and rotates, have the gas box of gathering because of the middle part fixed mounting of bull stick, gather the gas box and establish the positive middle part at supplementary flabellum group, the front end of gathering the gas box is provided with the opening, so engine during operation has partly air current to enter into through the opening that gathers gas box front end and gather in the gas box, the air inlet has been seted up because of gathering the inside of gas box again, the air inlet is seted up in the middle part wall of bull stick, can enter into the bull stick through the air inlet when the air current enters into gathering the gas box promptly, and finally carry away through the disappointing hole of bull stick right-hand member, realize the cooling processing to the bull stick, avoid the bull stick to be in high temperature state for a long time and take place thermal expansion and cause the deformation to cause the incident.
3. When the air current when the bull stick inside circulation, install the power pole because of the inside of bull stick is rotated through the bearing, the middle part fixed mounting of power pole has the gas fan of gathering, and gathers the gas fan and be the spill setting around the power pole, and the outer end setting of gathering the gas fan is in air inlet department, so the air current can drive when entering into the bull stick inside through the air inlet and gather the gas fan and rotate to pour the air current that passes through into fast and advance in the bull stick, thereby further improve the radiating efficiency to the bull stick.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is a rear view of the present invention;
FIG. 3 is a schematic view of the construction of the turbine of the present invention;
FIG. 4 is a schematic structural view of the gas gathering box of the present invention;
FIG. 5 is an enlarged view of a portion of the invention at A in FIG. 4;
in the figure: the fan comprises an outer cover 1, turbine fan blades 2, a rotating rod 3, an air gathering box 31, an air inlet 32, an air release hole 33, a power rod 34, an air gathering fan 35, an air blowing ring 36, a spiral groove 37, an expansion bag 38 and an auxiliary fan blade group 4.
Detailed Description
An aircraft engine turbine according to an embodiment of the present invention will be described below with reference to fig. 1 to 5.
As shown in fig. 1-5, the aircraft engine turbine according to the present invention includes a housing 1, turbine blades 2, a rotating rod 3, and an auxiliary blade group 4, wherein the rotating rod 3 is rotatably mounted inside the housing 1; the front end of the rotating rod 3 is fixedly provided with a turbine fan blade 2, and the outer surface of the middle part of the rotating rod 3 is fixedly provided with an auxiliary fan blade group 4; the diameter of the turbine fan blade 2 is larger than that of the auxiliary fan blade group 4; the auxiliary fan blade group 4 is arranged in a symmetrical shape at two ends, and the diameter of the fan blade of the auxiliary fan blade group 4 is set from small to large from the inner end to the outer end; when the engine turbine starts to operate, the diameter of the turbine fan blade 2 is larger than that of the auxiliary fan blade group 4, so that the turbine fan blade 2 of the engine turbine can pump air to the inner wall of the outer cover 1 when the engine turbine starts to operate, and in the process of rotation of the turbine fan blade 2, the auxiliary fan blade group 4 exists, so that the air pumped by the turbine fan blade 2 can be sucked by the auxiliary fan blade group 4 to be divided into a part, flows along the inner side of the outer cover 1, and the diameter of the fan blade of the auxiliary fan blade group 4 is set to be small from the inner end to the outer end due to the fact that the auxiliary fan blade group 4 is arranged to be symmetrical at two ends, so that the air flow pumped by the turbine fan blade 2 can be uniformly divided, the acting force of the air flow on the inner wall of the outer cover 1 is reduced, namely the temperature in the outer cover 1 is reduced, and rapid temperature rise of the rotating rod 3 caused by overhigh temperature in the outer cover 1 is avoided.
The middle part of the rotating rod 3 is fixedly provided with a gas gathering box 31; the air gathering box 31 is annular, the air gathering box 31 is arranged in the middle of the auxiliary fan blade group 4, an opening is formed in the front end of the air gathering box 31, and an air inlet 32 is formed in the air gathering box 31; the air inlet 32 is formed in the middle wall of the rotating rod 3; the interior of the rotating rod 3 is hollow, and air leakage holes 33 are uniformly formed in the right end wall of the rotating rod 3; the air release hole 33 is arranged in a circular shape; when the engine works to drive the turbine fan blades 2 and the auxiliary fan blade group 4 to rotate, the gas gathering box 31 is fixedly installed in the middle of the rotating rod 3, the gas gathering box 31 is arranged in the middle of the auxiliary fan blade group 4, and an opening is formed in the front end of the gas gathering box 31, so that a part of air flow enters the gas gathering box 31 through the opening in the front end of the gas gathering box 31 when the engine works, the air inlet 32 is formed in the gas gathering box 31, the air inlet 32 is formed in the middle wall of the rotating rod 3, namely, when the air flow enters the gas gathering box 31, the air flow enters the rotating rod 3 through the air inlet 32 and is finally conveyed out through the air leakage hole 33 in the right end of the rotating rod 3, the cooling treatment of the rotating rod 3 is realized, and the safety accident caused by the thermal expansion of the rotating rod 3 in a high-temperature state for a long time is avoided.
A power rod 34 is rotatably arranged in the rotating rod 3 through a bearing; the middle part of the power rod 34 is fixedly provided with an air gathering fan 35; the air gathering fan 35 is arranged around the power rod 34 in a concave shape, and the outer end of the air gathering fan 35 is arranged at the air inlet 32; when the air current when bull stick 3 inside circulation, install power bar 34 because of the inside of bull stick 3 is rotated through the bearing, the middle part fixed mounting of power bar 34 has the gas fan 35 of gathering, and gather gas fan 35 and be the spill setting around power bar 34, gather the outer end setting of gas fan 35 in air inlet 32 department, so the air current can drive when entering into bull stick 3 inside through air inlet 32 and gather gas fan 35 and rotate, and pour the air current that passes through into fast in advancing bull stick 3, thereby further improve the radiating efficiency to bull stick 3.
The inner wall of the gas gathering box 31 is fixedly connected with a blast ring 36; the middle part of the air blowing ring 36 is arranged in a convex arc shape, and two ends of the air blowing ring 36 are fixedly connected to the inner wall bulges of the air gathering box 31; when the air current is when gathering in the box 31 through gathering, because of gathering the inner wall fixedly connected with blast ring 36 of box 31, the middle part of blast ring 36 is the convex arc setting, and the both ends fixed connection of blast ring 36 is protruding at the inner wall of gathering box 31, so the air current gets into and gathers the air inlet 32 department that can be got into bull stick 3 by furthest because of the existence of blast ring 36 when box 31, has increased substantially promptly and has gathered the rotational speed of gas fan 35 to further improve the cooling effect to bull stick 3.
The inner wall of the air blowing ring 36 is provided with a spiral groove 37; when the gas gathering box 31 works, the spiral groove 37 is formed in the inner wall of the air blowing ring 36, so that when air flows enter the gas gathering box 31, the air flows can enter the air inlet 32 on the rotating rod 3 in a spiral mode due to the acting force of the spiral groove 37 on the air blowing ring 36, namely the acting force of the air flows is greatly improved, and the acting force of the gas gathering fan 35 is improved, so that the rotating speed of the gas gathering fan 35 is accelerated, and the cooling effect of the rotating rod 3 is improved.
The air blowing ring 36 is made of rubber materials, and an expansion bag 38 is fixedly connected inside the air blowing ring 36; the expansion bag 38 is annular, and the outer end of the expansion bag 38 is fixedly connected to the peripheral inner wall of the gas gathering box 31; when the blowing ring 36 works, because the blowing ring 36 is made of rubber materials, the expansion bag 38 is fixedly connected inside the blowing ring 36, the expansion bag 38 is annular, the outer end of the expansion bag 38 is fixedly connected to the inner wall of the periphery of the air gathering box 31, the blowing ring 36 is intermittently sunken towards the inner end when being extruded by air flow, namely, the expansion bag 38 is extruded, even if the blowing ring 36 instantly sends wind power to the air inlet 32 due to the resetting function of the expansion bag 38 when the acting force is reduced, namely, the air gathering fan 35 is ensured to be always in a high-speed running state, the air drainage effect is ensured, and the high-efficiency heat dissipation effect on the rotating rod 3 is achieved.
The specific working process is as follows:
when the engine turbine starts to operate, because the diameter of the turbine fan blade 2 is larger than that of the auxiliary fan blade group 4, the turbine fan blade 2 of the engine turbine can pump air to the inner wall of the outer cover 1 when the engine turbine starts to operate, and because the auxiliary fan blade group 4 exists in the process of the rotation of the turbine fan blade 2, the air pumped by the turbine fan blade 2 can be sucked by the auxiliary fan blade group 4 to be divided into a part and flows along the inner side of the outer cover 1, because the auxiliary fan blade group 4 is arranged in a symmetrical shape with two ends, and the diameter of the fan blade of the auxiliary fan blade group 4 is arranged from the inner end to the outer end to be large, the air flow pumped by the turbine fan blade 2 can be uniformly divided, so that the acting force of the air flow on the inner wall of the outer cover 1 is reduced, namely, the temperature in the outer cover 1 is reduced, the rapid temperature rise of the rotating rod 3 caused by the overhigh temperature in the outer cover 1 is avoided, when the engine operates to drive the turbine fan blade 2 and the auxiliary fan blade group 4 to rotate, because of the middle part fixed mounting of bull stick 3 has the box 31 of gathering gas, gather the box 31 of gathering gas and establish in the centre of supplementary flabellum group 4, the front end of gathering the box 31 is provided with the opening, so engine during operation has some air current to enter into through the opening that gathers the box 31 front end and gather in the box 31, again because of gathering the inside of box 31 and seted up air inlet 32, air inlet 32 is seted up in the middle part wall of bull stick 3, the air current can enter into the bull stick 3 through air inlet 32 when entering into gathering the box 31 promptly, and finally carry out through the disappointing hole 33 of bull stick 3 right-hand member, realize the cooling processing to bull stick 3, avoid the bull stick 3 to be in the high temperature state for a long time and take place thermal energy and cause the deformation and cause the incident.
While the present invention has been described with reference to the particular illustrative embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but is intended to cover various modifications, equivalent arrangements, and equivalents thereof, which may be made by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. The utility model provides an aeroengine turbine, includes dustcoat (1), turbine flabellum (2), bull stick (3) and supplementary flabellum group (4), its characterized in that: a rotating rod (3) is rotatably arranged in the outer cover (1); the front end of the rotating rod (3) is fixedly provided with a turbine fan blade (2), and the outer surface of the middle part of the rotating rod (3) is fixedly provided with an auxiliary fan blade group (4); the diameter of the turbine fan blade (2) is larger than that of the auxiliary fan blade group (4); the auxiliary fan blade group (4) is arranged to be symmetrical at two ends, and the diameter of the fan blade of the auxiliary fan blade group (4) is arranged from small to large from the inner end to the outer end;
the middle part of the rotating rod (3) is fixedly provided with a gas gathering box (31); the air gathering box (31) is annular, the air gathering box (31) is arranged in the middle of the auxiliary fan blade group (4), an opening is formed in the front end of the air gathering box (31), and an air inlet (32) is formed in the air gathering box (31); the air inlet (32) is formed in the middle wall of the rotating rod (3); the rotating rod (3) is hollow, and air release holes (33) are uniformly formed in the right end wall of the rotating rod (3); the air release hole (33) is arranged in a circular shape.
2. An aircraft engine turbine according to claim 1, wherein: a power rod (34) is rotatably arranged in the rotating rod (3) through a bearing; the middle part of the power rod (34) is fixedly provided with an air gathering fan (35); gather gas fan (35) and be the concave setting around power rod (34), gather the outer end setting of gas fan (35) and be in air inlet (32).
3. An aircraft engine turbine according to claim 1, wherein: the inner wall of the gas gathering box (31) is fixedly connected with a blast ring (36); the middle part of the air blowing ring (36) is arranged in a convex arc shape, and two ends of the air blowing ring (36) are fixedly connected to the inner wall protrusions of the air gathering box (31).
4. An aircraft engine turbine according to claim 3, wherein: the inner wall of the air blowing ring (36) is provided with a spiral groove (37).
5. An aircraft engine turbine according to claim 3, wherein: the air blowing ring (36) is made of rubber materials, and an expansion bag (38) is fixedly connected inside the air blowing ring (36); the expansion bag (38) is annular, and the outer end of the expansion bag (38) is fixedly connected to the peripheral inner wall of the gas gathering box (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911019930.0A CN110645052B (en) | 2019-10-24 | 2019-10-24 | Turbine of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911019930.0A CN110645052B (en) | 2019-10-24 | 2019-10-24 | Turbine of aircraft engine |
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| Publication Number | Publication Date |
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| CN110645052A CN110645052A (en) | 2020-01-03 |
| CN110645052B true CN110645052B (en) | 2022-07-05 |
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Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140174056A1 (en) * | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
| US20180045221A1 (en) * | 2016-08-15 | 2018-02-15 | General Electric Company | Strut for an aircraft engine |
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Effective date of registration: 20230106 Address after: 712, 7th floor, 288 Yangcun Road, choujiang street, Yiwu City, Jinhua City, Zhejiang Province (self declaration) Patentee after: Fengte (Zhejiang) new material Co.,Ltd. Address before: 230000 room 1202, building 7, Jinting, Wanke Forest Park, Guzhen Road, Luyang District, Hefei City, Anhui Province Patentee before: Zhou Yufan |
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