CN207470232U - Compressor turbine for aircraft engine - Google Patents
Compressor turbine for aircraft engine Download PDFInfo
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- CN207470232U CN207470232U CN201721642900.1U CN201721642900U CN207470232U CN 207470232 U CN207470232 U CN 207470232U CN 201721642900 U CN201721642900 U CN 201721642900U CN 207470232 U CN207470232 U CN 207470232U
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- turbo
- blade
- main body
- compressor turbine
- turbine
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Abstract
The utility model discloses a compressor turbine for an aero engine, which comprises a turbine body (1) and turbine blades (2). The turbine body (1) is cylindrical, and the turbine blades (2) are arranged on A plurality of cone-like flow passages (11) are uniformly arranged in the circumferential direction on the cylindrical side surface of the turbine body (1). In addition, a blade flow passage (21) and a blade flow passage (22) are opened inside the turbine blade (2), and the blade flow passage (21) and the blade flow passage (22) are both from the turbine The free end of the blade (2) extends toward the inside of the turbine body (1) until it communicates with the conical section (112) of the cone-like flow channel (11). The compressor turbine is made by 3D printing and is integrally formed, and successfully realizes a new complex structure under the premise of ensuring the strength of use.
Description
Technical field
The utility model belongs to aero-engine field, is related to the compressor turbine for aero-engine.
Background technology
Compressor turbine for aero-engine is one of core component of engine, and still, turbine is at high speed
Work in very high centrifugal force field, thus, it is ensured that turbine works normally, must just carry out turbine effectively cold
But.
Therefore, the cooling structure (or fluid channel) of turbine interior be related to it is most important.And for complicated new
Still, the compressor turbine of 3D printing is also not disclosed in type turbine, optimal selection during 3D printing in the prior art.
Utility model content
In order to overcome the above problem, present inventor has performed sharp study, using 3D printing technique obtain a kind of one into
The compressor turbine of type, wherein, class tapered runner 11 is provided in turbo main body 1, being provided with blade in turbo blade 2 leads to
Road 1 and blade path 2 22, and the blade path 1 and blade path 2 22 are realized with class tapered runner 11 and are connected
It is logical, in this way, the air ventilation passage (as shown in Figure 9) for being located at turbine interior and being connected with turbo blade can be obtained, realize
Cooling to turbine, so as to complete the utility model.
The utility model provides a kind of compressor impeller for aero-engine, is embodied in following：
(1) a kind of compressor turbine for aero-engine, wherein, the compressor turbine includes 1 He of turbo main body
Turbo blade 2, the turbo main body 1 is cylindrical, and the turbo blade 2 is set on the side of the cylindricality, wherein,
It is equably provided with multiple class tapered runners 11 along circumferential direction in the inside of the turbo main body 1, along turbine master
The radial direction of body 1, the class tapered runner 11 include hemisphere section 111 and round platform section 112 successively.
(2) compressor turbine according to above-mentioned (1), wherein,
The turbo blade 2 and the joint of the turbo main body 1 are set for chamfering；And/or
Adjacent round platform section 112 communicates with each other in free end.
(3) compressor turbine according to above-mentioned (2), wherein, it is opened at the upper surface of the turbo main body 1, axle center
Equipped with tubular trepanning 12, the tubular trepanning 12 is to 1 internal stretch of turbo main body.
(4) compressor turbine according to above-mentioned (3), wherein, in the inside of turbo main body 1, the tubular trepanning 12
It is connected by interface channel 13 with class tapered runner 11.
(5) compressor turbine according to above-mentioned (4), wherein, offer blade flow in the inside of the turbo blade 2
Road 1 and blade passage 2 22.
(6) compressor turbine according to above-mentioned (5), wherein, the blade passage 1 and blade passage 2 22 are equal
From the free end of turbo blade 2 to the internal stretch of turbo main body 1, until being connected with the round platform section 112 of class tapered runner 11.
(7) compressor turbine according to above-mentioned (6), wherein, it is offered on the surface of the turbo blade 2 multiple logical
Stomata 23, internal stretch from the venthole 23 to turbo blade 2, until connected with the blade passage 1.
(8) compressor turbine according to one of above-mentioned (1) to (7), wherein, on the 1 upper surface side of turbo main body
It is provided at edge in the multiple crescent shaped grooves 14 of centrifugation shape arrangement.
(9) compressor turbine according to above-mentioned (8), wherein, it is provided in the 1 lower face edge of turbo main body
Multiple counterbores 15, the multiple counterbore 15 are uniformly distributed along the circumferential direction of turbo main body 1.
(10) compressor turbine according to above-mentioned (9), wherein, the compressor turbine is obtained by 3D printing.
Description of the drawings
Fig. 1 shows the structure diagram of compressor turbine described in the utility model；
Fig. 2 shows the partial enlarged views of Fig. 1；
Fig. 3 shows the front view of compressor turbine described in the utility model；
Fig. 4 shows the vertical view of compressor turbine described in the utility model；
Fig. 5 shows the bottom view of compressor turbine described in the utility model；
Fig. 6 show A-A in Fig. 3 to schematic cross-section；
Fig. 7 shows the schematic cross-section of B-B direction in Fig. 6；
Fig. 8 shows the close-up schematic view of compressor turbine described in the utility model；
Fig. 9 shows the air ventilation passage schematic diagram inside compressor turbine described in the utility model.
Drawing reference numeral explanation：
1- turbo main bodies；11- class tapered runners；111- hemisphere sections；112- round platform sections；12- tubular trepannings；13- connections are logical
Road；14- crescent shaped grooves；15- counterbores；2- turbo blades；21- blade passages one；22- blade passages two；23- ventholes.
Specific embodiment
The utility model is further described below by drawings and embodiments.Pass through these explanations, this practicality
The characteristics of novel and advantage will become more apparent from clearly.Wherein, although the various aspects of embodiment are shown in the drawings,
But unless otherwise indicated, it is not necessary to attached drawing drawn to scale.
The utility model provides a kind of compressor turbine for aero-engine, as shown in Figure 1, it includes turbine master
Body 1 and turbo blade 2, wherein, the turbo main body 1 is cylindrical, and the turbo blade 2 is set on the side of the cylindricality,
And the turbo blade 2 and the joint of the turbo main body 1 are set for chamfering.
According to a kind of preferred embodiment of the utility model, as shown in fig. 6, in the inside of the turbo main body 1 along week
Multiple class tapered runners 11 are equably provided with to direction.
In further preferred embodiment, as shown in fig. 7, along the radial direction of turbo main body 1, preferably circumferentially side
Edge is to the radial direction in axle center, and the class tapered runner 11 is successively including hemisphere section 111 and round platform section 112.
In embodiment still more preferably, as shown in fig. 6, adjacent round platform section 112 communicates with each other in free end.
Wherein, by adjacent class tapered runner 11 in free end (i.e. at axle center) connection of round platform section 112, realization
Connection between class tapered runner 11.
According to a kind of preferred embodiment of the utility model, as shown in Figure 1 and Figure 7, in the upper end of the turbo main body 1
Tubular trepanning 12 is offered at face, axle center.
In further preferred embodiment, as shown in fig. 7, the tubular trepanning 12 is to 1 internal stretch of turbo main body.
In embodiment still more preferably, as shown in figs. 6-7, in the inside of turbo main body 1, the tubular is opened
Hole 12 is connected by interface channel 13 with class tapered runner 11.
In this way, the class tapered runner 11 being arranged on inside turbo main body 1 is realized and tubular trepanning 12 by interface channel 13
Connection, for airflow.
According to a kind of preferred embodiment of the utility model, as shown in Fig. 1~3 and Fig. 8, opened in the turbo blade
Equipped with blade passage 1 and blade passage 2 22.
In further preferred embodiment, the blade passage 1 and blade passage 2 22 are from turbo blade 2
Internal stretch from free end to turbo main body 1.
In embodiment still more preferably, as shown in figure 8, the blade passage 1 and blade passage 2 22 are equal
It extends to inside turbo main body 1, until being connected with the round platform section 112 of class tapered runner 11.
According to a kind of preferred embodiment of the utility model, as shown in figure 8, being opened up on the surface of the turbo blade 2
There are multiple ventholes 23.
In further preferred embodiment, internal stretch from the venthole 23 to turbo blade 2, until with it is described
Blade passage 1 connects.
In this way, realize turbo blade 2 and the air ventilation passage (as shown in Figure 9) inside turbo main body 1.Wherein, it is interior
On the one hand the gas channel of portion's setting can be the turbine loss of weight, turbine on the other hand can be cooled down, when high pressure draught passes through
When flowing to compressor turbine inside axial diffuser and turbine wheel shaft, efficiently turbo blade can be cooled down (because of compression
Machine turbine is chronically in thermal-flame, and effectively cooling can improve turbine life)；Third, when high-speed flow passes through venthole
When 23, one propulsive thrust of turbine can be given so that micro- spray work capacity conversion ratio improves.
In the utility model, the venthole 23 on turbo blade is the equal of minim channel, can strengthen turbine
The cooling of blade.
According to a kind of preferred embodiment of the utility model, as shown in Fig. 1~2 and Fig. 4, in the turbo main body 1
Multiple crescent shaped grooves 14 are provided at end face edge.
In further preferred embodiment, as shown in figure 4, the multiple crescent shaped groove 14 is in centrifugation shape arrangement.
Wherein, on the face that crescent shaped groove circumference uniform distribution faces combustion chamber in compressor turbine, high-speed fuel gas is from burning
After room comes out, turbo blade is acted on, turbine rotation is then driven, then turbine wheel shaft is driven to rotate again, last driving compression again
Machine impeller rotate, as long as therefore it is micro- spray start after, you can formed a ringing.Set crescent recessed on compressor turbine
Slot, is mainly used for the high-speed flow that discrete vertical is acted in turbo main body 1, and theoretical overdraught all acts on turbo blade
Upper efficiency is highest, but having fraction can act in turbo main body 1, can give compressor turbine one very big in this way
Axial force, therefore crescent shaped groove is set, dispersible air-flow reduces air-flow to the axial force of compressor turbine.Secondly effect
If be high temperature and high speed combustion gas long duration of action at the tubular trepanning 12 of turbine, be to have a significant impact for turbine life, setting
Crescent shaped groove also can avoid high-temperature fuel gas from entering at tubular trepanning 12.
According to a kind of preferred embodiment of the utility model, as shown in Fig. 1~2 and Fig. 4, under the turbo main body 1
Multiple counterbores 15 are provided at end face edge.
In further preferred embodiment, as shown in figure 5, circumferential direction side of the multiple counterbore 15 along turbo main body 1
To being uniformly distributed.
Wherein, locating when functioning as assembling of setting counterbore 15 is used.
According to a kind of preferred embodiment of the utility model, the compressor turbine is obtained by 3D printing.
In the utility model, the upper surface of the turbo main body refers to the end face with 12 homonymy of tubular trepanning, under described
End face refers to the end face with tubular trepanning 12 backwards.
Advantageous effect includes possessed by the utility model：
(1) compressor turbine is made using 3D printing, is integrally formed；
(2) compressor turbine successfully realizes novel complex structure under the premise of use intensity is ensured；
(3) there is the air ventilation passage (as shown in Figure 9) connected with turbo blade inside the compressor turbine, it is real
Now to effective cooling of turbine.
In the description of the present invention, it should be noted that term the instructions such as " on ", " under " " interior " orientation or position
Relationship is for only for ease of description the utility model and simplifies description rather than instruction or imply that signified device or element are necessary
With specific orientation, with specific azimuth configuration and operation, therefore it is not intended that limitation to the utility model.
The utility model is illustrated above in association with preferred embodiment, but these embodiments are only models
Example property, only play the role of illustrative.On this basis, a variety of replacements and improvement can be carried out to the utility model, these
It each falls in the scope of protection of the utility model.
Claims (10)
1. a kind of compressor turbine for aero-engine, which is characterized in that the compressor turbine includes turbo main body (1)
With turbo blade (2), the turbo main body (1) is cylindrical, and the turbo blade (2) is set on the side of the cylindricality,
In,
Multiple class tapered runners (11) are equably provided with along circumferential direction in the inside of the turbo main body (1), along turbine master
The radial direction of body (1), the class tapered runner (11) include hemisphere section (111) and round platform section (112) successively.
2. compressor turbine according to claim 1, which is characterized in that
The turbo blade (2) and the joint of the turbo main body (1) are set for chamfering；And/or
Adjacent round platform section (112) communicates with each other in free end.
3. compressor turbine according to claim 2, which is characterized in that in the upper surface of the turbo main body (1), axle center
Place offers tubular trepanning (12), and the tubular trepanning (12) is to turbo main body (1) internal stretch.
4. compressor turbine according to claim 3, which is characterized in that wherein, described in the inside of turbo main body (1)
Tubular trepanning (12) is connected by interface channel (13) with class tapered runner (11).
5. compressor turbine according to claim 4, which is characterized in that offered in the inside of the turbo blade (2)
Blade passage one (21) and blade passage two (22).
6. compressor turbine according to claim 5, which is characterized in that the blade passage one (21) and blade passage two
(22) from the free end of turbo blade (2) to the internal stretch of turbo main body (1), until the circle with class tapered runner (11)
Platform section (112) connects.
7. compressor turbine according to claim 6, which is characterized in that offered on the surface of the turbo blade (2)
Multiple ventholes (23), internal stretch from the venthole (23) to turbo blade (2), until with the blade passage one (21)
Connection.
8. the compressor turbine according to one of claim 1 to 7, wherein, in the turbo main body (1) upper surface edge
It is provided in the multiple crescent shaped grooves (14) of centrifugation shape arrangement.
9. compressor turbine according to claim 8, wherein, it is provided in the turbo main body (1) lower face edge
Multiple counterbores (15), the multiple counterbore (15) are uniformly distributed along the circumferential direction of turbo main body (1).
10. compressor turbine according to claim 9, wherein, the compressor turbine is obtained by 3D printing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721642900.1U CN207470232U (en) | 2017-11-30 | 2017-11-30 | Compressor turbine for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721642900.1U CN207470232U (en) | 2017-11-30 | 2017-11-30 | Compressor turbine for aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207470232U true CN207470232U (en) | 2018-06-08 |
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ID=62257372
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721642900.1U Active CN207470232U (en) | 2017-11-30 | 2017-11-30 | Compressor turbine for aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207470232U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653674A (en) * | 2021-09-07 | 2021-11-16 | 大连海事大学 | Compressor with blade diffuser and cooling channel |
-
2017
- 2017-11-30 CN CN201721642900.1U patent/CN207470232U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653674A (en) * | 2021-09-07 | 2021-11-16 | 大连海事大学 | Compressor with blade diffuser and cooling channel |
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