High-efficiency aeronautical turbine blade with pneumatic optimization design

Abstract

The utility model provides a high-efficiency aeronautical turbine blade with pneumatic optimization design, which belongs to the field of aeronautical turbine blades, and aims to solve the problems that the blade profile and the torsion rule of the blade are not fine, the air flow cannot reach an ideal flowing state, and energy loss is caused, the high-efficiency aeronautical turbine blade comprises a blade central shaft, twelve turbine fan blades are welded to the arc-shaped outer side wall of the blade center shaft in an annular array mode, a fairing is connected to the front side wall of the blade center shaft in a threaded mode, and multiple layers of filter screens are installed between the rear side wall of the fairing and the front side wall of the blade center shaft. According to the high-efficiency aviation turbine blade with the pneumatic optimization design, the flow guide microgrooves are formed in the pressure surface and the suction surface of the turbine blade, the airflow adhesion performance of the surface of the turbine blade is improved, the pneumatic efficiency is improved, airflow circulation is provided for each part through cooperation of the air inlet branch pipe and the air outlet branch pipe, so that the turbine blade is efficiently cooled, and the service life of the turbine blade is prolonged. The turbine blades are effectively protected against high-temperature damage, and it is ensured that the turbine blades can keep good mechanical performance in the high-temperature and high-pressure working environment.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation turbine blade technical field especially relates to the high -efficient aviation turbine blade of aerodynamic optimization design. BACKGROUND

[0002] In the field of aerospace, as the core power device of the aircraft, the performance improvement of the aviation turbine engine is crucial to the development of the entire aviation industry, and as the key component of the aviation turbine engine, the turbine blade directly affects the efficiency, power output and reliability of the engine and other key performance indicators, the existing aviation turbine blade's blade type and torsion law are not fine enough, which leads to the fact that the airflow cannot achieve the ideal flow state when flowing through the blade channel, because the traditional blade does not fully consider the diversity of airflow angle and speed distribution, when high-speed airflow impacts the blade, a local high-pressure area is formed, which in turn causes irreversible loss of energy, and when the blade expands and contracts due to heat, the mechanical properties of the blade are affected. SUMMARY

[0003] The utility model discloses a high -efficient aviation turbine blade of aerodynamic optimization design aims at providing the high -efficient aviation turbine blade of aerodynamic optimization design to solve the problem of the blade type and torsion law of the existing aviation turbine blade not being fine enough in the background art, which leads to the fact that the airflow cannot achieve the ideal flow state when flowing through the blade channel, a local high-pressure area is formed, which in turn causes irreversible loss of energy, and when the blade expands and contracts due to heat, the mechanical properties of the blade are affected.

[0004] The purpose and effect of the high -efficient aviation turbine blade of aerodynamic optimization design of the utility model are achieved by the following specific technical means:

[0005] The high -efficient aviation turbine blade of aerodynamic optimization design, wherein the high -efficient aviation turbine blade of aerodynamic optimization design includes the blade center shaft, twelve turbine blades are annularly arrayed and welded on the arc outer side wall of the blade center shaft, a fairing is threadedly connected to the front side wall of the blade center shaft, a plurality of filter screens are installed between the rear side wall of the fairing and the front side wall of the blade center shaft, an air inlet distributor disc and an air outlet diffuser disc are respectively fixedly installed on the front wall rear side and the rear side rear side of the blade center shaft.

[0006] Further, twelve curved blade roots are fixedly connected to the arc outer side wall of the blade center shaft in an annular array, an annular outer connecting protrusion is fixedly connected to the outer side wall of the blade center shaft, a blocking pad is arranged at the connection between the rear end of the outer connecting protrusion and the front side wall of the blade center shaft, a plurality of filter screens are inserted into the outer connecting protrusion in front of the blocking pad, and a through connecting shaft hole is formed in the middle of the front and rear side walls of the blade center shaft.

[0007] Further, the fairing is conical, the rear wall of the fairing is concave, and six air inlet cone holes are arranged in an annular array in the rear wall of the fairing and are front wide and rear narrow.

[0008] Further, an air inlet channel is arranged in the front wall of the air inlet distribution disc, the air inlet channel is inserted into the blocking pad of the blade center shaft, twelve distribution air pipes are connected to the outer wall of the air inlet distribution disc in an annular array, and the distribution air pipes are connected to the curved blade roots of the outer wall of the blade center shaft.

[0009] Further, a circular hole is arranged in the middle of the air outlet diffusion disc and penetrates the connecting shaft hole of the blade center shaft, the rear wall of the air outlet diffusion disc is an open aggregated air pipe, twelve air outlet channels are connected to the outer wall of the air outlet diffusion disc in an annular array, and the air outlet channels are connected to the curved blade roots of the outer wall of the blade center shaft.

[0010] Further, the inside of the turbine fan blade is hollow, the bottom of the turbine fan blade is fixedly connected to the curved blade root end of the blade center shaft, the pressure surface and the suction surface of the turbine fan blade are both provided with inclined flow guide micro grooves at equal intervals, the inside of the turbine fan blade is provided with inclined inner partitions at equal intervals, the inside of the turbine fan blade is fixedly provided with an air inlet branch pipe, a circular hole is arranged in the front wall of the air inlet branch pipe close to the upper end surface of the inner partition, the inside of the turbine fan blade is fixedly provided with an air outlet branch pipe, and a circular hole is arranged in the rear wall of the air outlet branch pipe close to the lower end surface of the inner partition.

[0011] The utility model provides a high -efficient aviation turbine blade of pneumatic optimization design has the following beneficial effects:

[0012] 1. By arranging flow guide micro grooves on the pressure surface and the suction surface of the turbine fan blade, the development of the boundary layer is effectively controlled, the airflow adhesion performance of the turbine fan blade surface is improved, the boundary layer separation is reduced, the aerodynamic efficiency is improved, the inside of the turbine fan blade is spaced into multiple parts by the inner partitions installed at equal intervals, airflow circulation is provided for each part by the cooperation of the air inlet branch pipe and the air outlet branch pipe, the turbine fan blade is efficiently cooled, the turbine fan blade is effectively protected from high temperature damage, and the turbine fan blade can maintain good mechanical properties in a high temperature and high pressure working environment.

[0013] 2. By fixedly connecting twelve curved blade roots to the arc outer wall of the blade center shaft, the turbine fan blade changes in a specific curve under the cooperation of the curved blade roots and the turbine fan blade, the airflow is more in line with the ideal flow state at the curved blade roots, the airflow separation is reduced, and the outer connecting protrusion for connecting the fairing is fixedly connected to the front wall of the blade center shaft, so that the air inlet cone holes are arranged in the connecting fairing to blow air into the blade center shaft, the multi-layer filter screen is arranged in the outer connecting protrusion, the gas entering the air inlet cone holes is filtered through the multi-layer filter screen, and the blade center shaft is prevented from being damaged by sundries. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 is a front side shaft view structural schematic diagram of the utility model;

[0015] Figure 2 is a rear side shaft view structural schematic diagram of the utility model;

[0016] Figure 3 is a whole split structural schematic diagram of the utility model;

[0017] Figure 4 is a blade center shaft and fairing cut structure schematic diagram of the utility model;

[0018] Figure 5 is an air inlet distribution disc and air outlet diffusion disc cut structure schematic diagram of the utility model;

[0019] Figure 6 is a turbine fan blade cut structure schematic diagram of the utility model;

[0020] Figure 7 is an A place enlarged structure schematic diagram of the utility model Figure 6 .

[0021] In the drawing, the corresponding relationship of component name and drawing number is:

[0022] 1, blade center shaft; 101, curved blade root; 102, outer connecting protrusion; 103, blocking pad; 104, connecting shaft hole; 2, multilayer filter screen; 3, fairing; 301, air inlet cone hole; 4, air inlet distribution disc; 401, air inlet; 402, distribution air pipe; 5, air outlet diffusion disc; 501, polymerization air pipe; 502, air outlet; 6, turbine fan blade; 601, guide micro groove; 602, inner partition plate; 603, air inlet branch pipe; 604, air outlet branch pipe. DETAILED DESCRIPTION

[0023] The embodiment of the utility model is further described in detail below in combination with the drawings and examples.

[0024] Example one:

[0025] As shown in the drawings: Figure 1 Figure 7

[0026] ​​The utility model provides pneumatic optimization design's high -efficient aviation turbine blade, including: blade center shaft 1, twelve turbine fan blade 6 are welded with annular array on the arc outer side wall of blade center shaft 1, the front side wall of blade center shaft 1 is connected with the fairing 3 of screw thread, the rear side wall of fairing 3 and the front side wall of blade center shaft 1 are installed with multilayer filter screen 2, the front wall rear side of blade center shaft 1 and rear side rear side are fixedly installed with air inlet distribution disc 4 and air outlet diffusion disc 5 respectively, twelve curved blade roots 101 are fixedly connected with annular array on the arc outer side wall of blade center shaft 1, the outer side wall of blade center shaft 1 is fixedly connected with the annular outer connecting protrusion 102 of ring, the rear end of outer connecting protrusion 102 and blade center shaft 1 front side wall junction is equipped with the blocking pad 103, and the outer connecting protrusion 102 of blocking pad 103 front side inserts with multilayer filter screen 2, the front and rear side wall of blade center shaft 1 middle part is equipped with the connecting shaft hole 104 of through, the fairing 3 is conical, the rear side wall of fairing 3 is concave, the rear side wall of fairing 3 is equipped with six air inlet cone hole 301 with annular array, air inlet cone hole 301 is wide in front and narrow in back, specific effect, through the fixed connection of twelve curved blade roots 101 on the arc outer side wall of blade center shaft 1, under the cooperation of curved blade root 101 and turbine fan blade 6, make turbine fan blade 6 present specific curve change, can make the airflow more in accord with ideal flow state at curved blade root 101, reduce airflow separation, and the outer connecting protrusion 102 for connecting fairing 3 is fixedly connected on the front side wall of blade center shaft 1, to place multilayer filter screen 2 in outer connecting protrusion 102 through the establishment of air inlet cone hole 301 in connecting fairing 3 and blowing up in blade center shaft 1, the gas of air inlet cone hole 301 enters can be filtered through multilayer filter screen 2, avoid sundries to cause blade center shaft 1 damage.

[0027] The inner part of the turbine fan blade 6 is hollow, the bottom of the turbine fan blade 6 is fixedly connected to the end of the curved blade root 101 of the blade center shaft 1, the pressure surface and the suction surface of the turbine fan blade 6 are both provided with an inclined flow guide micro groove 601 at equal intervals, the inner part of the turbine fan blade 6 is provided with an inclined inner partition plate 602 at equal intervals, the inner part of the turbine fan blade 6 is fixedly provided with an air inlet branch pipe 603, a circular hole is formed in the front side wall of the air inlet branch pipe 603 close to the upper end surface of the inner partition plate 602, the inner part of the turbine fan blade 6 is fixedly provided with an air outlet branch pipe 604, a circular hole is formed in the rear side wall of the air outlet branch pipe 604 close to the lower end surface of the inner partition plate 602, the specific effect is that the flow guide micro groove 601 is formed on the pressure surface and the suction surface of the turbine fan blade 6, so as to effectively control the development of the boundary layer, improve the airflow adhesion performance of the surface of the turbine fan blade 6, reduce the boundary layer separation, improve the aerodynamic efficiency, and the inner partition plate 602 provided in the inner part of the turbine fan blade 6 at equal intervals divides the inner part of the turbine fan blade 6 into multiple parts at equal intervals, so that the air inlet branch pipe 603 and the air outlet branch pipe 604 cooperate to provide airflow circulation for each part, so as to efficiently cool the turbine fan blade 6, effectively protect the turbine fan blade 6 from high temperature damage, and ensure that the turbine fan blade 6 can maintain good mechanical properties in a high temperature and high pressure working environment.

[0028] The front side wall of the air inlet distribution disc 4 is provided with an air inlet channel 401, the air inlet channel 401 is inserted into the blocking pad plate 103 of the blade center shaft 1, and twelve distribution air pipes 402 are connected to the outer side wall of the air inlet distribution disc 4 in a ring array, the distribution air pipes 402 are connected to the curved blade root 101 of the outer side wall of the blade center shaft 1, and the specific effect is that the air inlet channel 401 is fixedly installed on the front wall of the blade center shaft 1, and the air inlet channel 401 and the outer connecting protrusion 102 on the front side of the blade center shaft 1 are corresponded, so as to realize the circulation of airflow, then the distribution air pipes 402 on the outer side wall of the air inlet distribution disc 4 supply air to the air inlet branch pipe 603 of the turbine fan blade 6, so as to perform heat dissipation operation on the turbine fan blade 6 through high-speed airflow, and prevent the turbine fan blade 6 from being affected by thermal expansion and cold contraction to disturb the airflow.

[0029] The middle part of the air outlet diffusion disc 5 is provided with a circular hole which penetrates through the connecting shaft hole 104 of the blade center shaft 1, the rear side wall of the air outlet diffusion disc 5 is an open type aggregation pipe 501, and twelve air outlet channels 502 are connected to the outer side wall of the air outlet diffusion disc 5 in a ring array, the air outlet channels 502 are connected to the curved blade root 101 of the outer side wall of the blade center shaft 1, and the specific effect is that the air outlet channels 502 of the air outlet diffusion disc 5 are connected with the air outlet branch pipe 604 of the turbine fan blade 6, so as to realize the efficient circulation of air in the turbine fan blade 6.

[0030] The specific use mode and effect of the embodiment are as follows:

[0031] In the use of the high-efficiency aviation turbine blade of the aerodynamic optimization design, through the fixed connection of twelve curved blade roots 101 on the arc outer wall of the blade center shaft 1, the turbine fan blade 6 is changed in a specific curve under the cooperation of the curved blade root 101 and the turbine fan blade 6, which can make the airflow more in line with the ideal flow state at the curved blade root 101, reduce airflow separation, and the outer connecting protrusion 102 for connecting the fairing 3 is fixedly connected on the front wall of the blade center shaft 1, so that the air is blown into the blade center shaft 1 by opening the air inlet cone hole 301 in the connecting fairing 3, the multi-layer filter screen 2 is placed in the outer connecting protrusion 102, the gas entering the air inlet cone hole 301 can be filtered through the multi-layer filter screen 2, avoiding the damage of sundries to the blade center shaft 1, the flow guide micro groove 601 is opened on the pressure surface and the suction surface of the turbine fan blade 6, so as to effectively control the development of the boundary layer, improve the airflow adhesion performance of the turbine fan blade 6 surface, reduce the boundary layer separation, improve the aerodynamic efficiency, and the inner partition plate 602 installed equidistantly inside the turbine fan blade 6 equidistantly separates the inside of the turbine fan blade 6 into multiple parts, so that each part is provided with airflow circulation through the cooperation of the air inlet branch pipe 603 and the air outlet branch pipe 604, in order to efficiently cool the turbine fan blade 6, effectively protect the turbine fan blade 6 from high temperature damage, ensure that the turbine fan blade 6 can maintain good mechanical properties in high temperature and high pressure working environment, the air inlet channel 401 is fixedly installed on the rear side of the front wall of the blade center shaft 1, and the air inlet channel 401 and the outer connecting protrusion 102 on the front side of the blade center shaft 1 are corresponded, so as to realize the circulation of airflow, then the air inlet branch pipe 603 of the turbine fan blade 6 is supplied with air through the air distribution pipe 402 of the air inlet distribution disc 4, so as to cool the turbine fan blade 6 through high-speed airflow, prevent the turbine fan blade 6 from being affected by thermal expansion and cold contraction to disturb the airflow, and the air outlet channel 502 of the air outlet diffusion disc 5 is connected with the air outlet branch pipe 604 of the turbine fan blade 6, realizing the efficient circulation of air inside the turbine fan blade 6.

[0032] Example two:

[0033] By designing the rear wall of the air outlet diffusion disc 5 to be diffused, the airflow can be guided to the outside of the engine, avoiding the influence of the exhaust airflow of the air outlet diffusion disc 5 on the engine cooling.

Claims

1. A high performance gas turbine blade aerodynamically optimised in design, characterised in that: The utility model provides a kind of turbine blade, including blade center shaft (1), twelve turbine blades (6) are welded in annular array on the arc outer side wall of the blade center shaft (1), the front side wall of blade center shaft (1) is threadedly connected with fairing (3), and multiple layers of filter screen (2) are installed between the rear side wall of fairing (3) and the front side wall of blade center shaft (1), the front side of the rear side of blade center shaft (1) is fixedly installed with air inlet distributor (4) and air outlet diffuser (5) respectively.

2. The aerodynamically optimised high performance aero turbine blade of claim 1, wherein: The utility model provides a kind of turbine blade, including blade center shaft (1), twelve turbine blades (6) are welded in annular array on the arc outer side wall of the blade center shaft (1), the front side wall of blade center shaft (1) is threadedly connected with fairing (3), and multiple layers of filter screen (2) are installed between the rear side wall of fairing (3) and the front side wall of blade center shaft (1), the front side of the rear side of blade center shaft (1) is fixedly installed with air inlet distributor (4) and air outlet diffuser (5) respectively.

3. The aerodynamically optimised high performance aero turbine blade of claim 1, wherein: The utility model provides a kind of turbine blade, including blade center shaft (1), twelve turbine blades (6) are welded in annular array on the arc outer side wall of the blade center shaft (1), the front side wall of blade center shaft (1) is threadedly connected with fairing (3), and multiple layers of filter screen (2) are installed between the rear side wall of fairing (3) and the front side wall of blade center shaft (1), the front side of the rear side of blade center shaft (1) is fixedly installed with air inlet distributor (4) and air outlet diffuser (5) respectively.

4. The aerodynamically optimised high performance aero turbine blade of claim 1, wherein: The utility model provides a kind of turbine blade, including blade center shaft (1), twelve turbine blades (6) are welded in annular array on the arc outer side wall of the blade center shaft (1), the front side wall of blade center shaft (1) is threadedly connected with fairing (3), and multiple layers of filter screen (2) are installed between the rear side wall of fairing (3) and the front side wall of blade center shaft (1), the front side of the rear side of blade center shaft (1) is fixedly installed with air inlet distributor (4) and air outlet diffuser (5) respectively.

5. The aerodynamically optimised high performance aero turbine blade as claimed in claim 1, wherein: The utility model provides a kind of turbine blade, including blade center shaft (1), twelve turbine blades (6) are welded in annular array on the arc outer side wall of the blade center shaft (1), the front side wall of blade center shaft (1) is threadedly connected with fairing (3), and multiple layers of filter screen (2) are installed between the rear side wall of fairing (3) and the front side wall of blade center shaft (1), the front side of the rear side of blade center shaft (1) is fixedly installed with air inlet distributor (4) and air outlet diffuser (5) respectively.

6. The aerodynamically optimised high performance aero turbine blade of claim 1, wherein: The utility model provides a kind of turbine blade, including blade center shaft (1), twelve turbine blades (6) are welded in annular array on the arc outer side wall of the blade center shaft (1), the front side wall of blade center shaft (1) is threadedly connected with fairing (3), and multiple layers of filter screen (2) are installed between the rear side wall of fairing (3) and the front side wall of blade center shaft (1), the front side of the rear side of blade center shaft (1) is fixedly installed with air inlet distributor (4) and air outlet diffuser (5) respectively.

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