CN206352530U - A kind of guider - Google Patents
A kind of guider Download PDFInfo
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- CN206352530U CN206352530U CN201621492763.3U CN201621492763U CN206352530U CN 206352530 U CN206352530 U CN 206352530U CN 201621492763 U CN201621492763 U CN 201621492763U CN 206352530 U CN206352530 U CN 206352530U
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- outer shroud
- inner disc
- installation portion
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Abstract
The utility model belongs to miniature turbine jet engines technical field, more particularly to a kind of guider, including outer shroud, inner disc and guide vane；Outer shroud includes outer shroud cylinder, sets annular installation portion with outer shroud cylinder coaxial line, and transition part is connected between annular installation portion and outer shroud cylinder, circumferentially spaced on the side wall of annular installation portion to be provided with several outer shroud connecting holes；Inner disc is cylindrical in shape, and is surrounded in inner disc and annular web is provided with cavity, and the outward flange of annular web is fixedly connected with the madial wall of inner disc, and boss is provided with the side of the close annular installation portion of the central through hole of inner disc.Annular installation portion is directly fixedly connected with engine housing, it is used to being fixedly connected with and positioning bearing chamber in the boss of central through hole sidepiece, entity connection is formed between annular web and inner disc can not only greatly improve the structural strength of guider, the jet pipe of the turbine rotor and rear portion that are also prevented from being located inside guider is heated excessive, it is possible to increase thrust performance.
Description
Technical field
The utility model belongs to miniature turbine jet engines technical field, more particularly to a kind of guider.
Background technology
Turbojet is a kind of turbogenerator, is characterized in that being completely dependent on combustion gas body produces thrust, generally uses
Make the power of high-speed aircraft.Turbojet is divided into centrifugal and two kinds of axial-flow type.Turbojet is according to " work
The pattern of circulation " is operated, its inspiration air from air, air is compressed and heating process after obtain energy and momentum,
The air for obtaining energy and momentum afterwards is discharged from propelling nozzle, when high-speed gas spray engine, while with action pneumatic
Machine and turbine continue to rotate, and maintain working cycles.
The later stage nineties in last century, along with reaching its maturity and consummate for large-scale turbojet technology, abroad
Occur in that dozens of thrust with the product of the miniature turbine jet engines of subordinate successively.Miniature turbine jet engines product quilt
It is widely used in military, civilian different field, is played an important role in future war, for example, applies in micro-unmanned war
In bucket machine.The subject that miniature turbine jet engines design is related to includes：Aerodynamics, Combustion, engine structure intensity
, mechanics, autonetics etc..
Guider is the important component of miniature turbine jet engines, and the effect of guider is the height for discharging combustion chamber
Warm gases at high pressure are depressured, and improve air velocity, while changing the direction of advance of air-flow, it is embedded in from radial direction flow direction
The turbine interior of guider central interior.The structure of guider influences on key performances such as the thrusts of miniature turbine jet engines
It is larger, therefore, a kind of guider how is designed so that the key performance such as thrust of miniature turbine jet engines is obtained greatly
Raising compares concern as people.
Utility model content
The purpose of this utility model is to provide a kind of guider, can not only improve miniature turbine jet engines thrust
Performance, but also can improve the structural strength of guider, plays heat-insulated effect, prevent from being located at turbine inside guider,
It is excessive that the jet pipe and rear axle at rear portion bear heat.
The utility model is achieved in that a kind of guider, and the guider includes outer shroud, inner disc and fixed company
It is connected on guide vane between the two；The outer shroud includes outer shroud cylinder, sets annular installation portion with outer shroud cylinder coaxial line,
Transition part is connected between annular installation portion and the outer shroud cylinder, it is circumferentially spaced on the side wall of the annular installation portion
It is provided with several outer shroud connecting holes；The inner disc is cylindrical in shape, and is surrounded in the inner disc and annular web is provided with cavity, described
The outward flange of annular web is fixedly connected with the madial wall of the inner disc, is pacified in the central through hole of the inner disc close to the annular
The side in dress portion is provided with boss.
As an improvement, the boss is provided with multiple, divides equally setting along the circumference of the central through hole of the inner disc.
As an improvement, the boss is provided with two, the both sides of the corresponding central through hole for being arranged on the inner disc.
As an improvement, the external diameter of the annular installation portion of the outer shroud is 185~190 millimeters, and internal diameter is 183~185
Millimeter, the internal diameter of the outer shroud cylinder is 145~147 millimeters, and the external diameter of the inner disc is 98~100 millimeters, the annular web
External diameter be 95~98 millimeters, a diameter of 47~49 millimeters of the central through hole of the annular web.
As an improvement, the internal diameter of the outer shroud is 184 millimeters, and the internal diameter of the outer shroud cylinder is 146 millimeters, the ring
A diameter of 48.2 millimeters of the central through hole of shape web.
As an improvement, the outer shroud connecting hole is provided with four, and the circumference along the annular installation portion divides equally setting,
Its aperture is 4 millimeters.
As an improvement, the angle between the guide vane and the inner disc radial direction is 65~70 degree.
As an improvement, the guide vane is 24.
As an improvement, the thickness of each guide vane is 1~3 millimeter, and the guide vane is in the outer shroud
Length between the inner disc outward flange is 21~23 millimeters.
As a result of said structure, the guider that the utility model is provided includes outer shroud, inner disc and is fixedly connected on
Guide vane between the two；Outer shroud includes outer shroud cylinder, sets annular installation portion with outer shroud cylinder coaxial line, annular installation portion with
Transition part is connected between outer shroud cylinder, it is circumferentially spaced on the side wall of annular installation portion to be provided with several outer shroud connecting holes；
Inner disc is cylindrical in shape, and is surrounded in inner disc and annular web is provided with cavity, the outward flange of annular web and the madial wall of inner disc are fixed
Connection, boss is provided with the side of the close annular installation portion of the central through hole of inner disc.The annular installation portion of the outer shroud of guider is straight
Connect and be fixedly connected with engine housing, boss is provided with the side of the close annular installation portion of the central through hole of inner disc, for fixing
Connection and positioning bearing chamber, are fixedly connected and position very convenient, and inner disc is surrounded in cavity provided with annular web, annular abdomen
Entity connection is formed between plate and inner disc can not only greatly improve the structural strength of guider, additionally it is possible to play heat-insulated work
With, can prevent be located at guider inside turbine rotor and rear portion jet pipe be heated it is excessive, it is possible to increase miniature turbine spray
Gas motor power performance.
Brief description of the drawings
Fig. 1 is the cross section structure diagram of guider of the present utility model；
Fig. 2 is the left view structural representation of guider of the present utility model；
Fig. 3 is the right side structural representation of guider of the present utility model；
Wherein, 11, outer shroud, 111, outer shroud cylinder, 112, annular installation portion, 113, outer shroud connecting hole, 114, transition part, 12,
Inner disc, 13, guide vane, 14, annular web, 141, Cooling Holes, 15, boss.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only to explain
The utility model, is not used to limit the utility model.
Before the one end for defining the air inlet of miniature turbine jet engines first is, after one end of jet is, the miniature turbine
Jet engine include shell, be arranged on the front end of shell and be fixedly connected with its end impeller cover, be arranged on shell
Front end and the guider being fixedly connected with its end, the sky that the cavity surrounded in impeller cover and the leading section of shell are surrounded
Intracavitary is provided with compressor impeller, and diffuser, burner and bearing block, bearing block are provided with the cavity surrounded of shell
Through burner, its one end is connected with diffuser, and the other end is connected with guider.
From Fig. 1 to Fig. 3, guider includes outer shroud 11, and the outer shroud 11 includes outer shroud cylinder 111, coaxial with outer shroud tin 111
Line sets annular installation portion 112, and transition part 114 is connected between annular installation portion 112 and outer shroud cylinder 111, in annular installation
It is circumferentially spaced on the side wall in portion 112 to be provided with several outer shroud connecting holes 113, in the present embodiment, the annular peace of outer shroud 11
The outer diameter A in dress portion 112 is 185~190 millimeters, and internal diameter B is 183~185 millimeters, preferably 184 millimeters, outer shroud connecting hole
113 are provided with four, and the circumference along annular installation portion 112 divides equally setting, and its aperture is 4 millimeters, and the internal diameter C of outer shroud cylinder 111 is
145~147 millimeters, preferably 146 millimeters；Tubular inner disc 12, the inner disc 12 is arranged on outer shroud 11 and surrounded in cavity
And with its coaxial line of outer shroud 11, in the present embodiment, the outer diameter D of inner disc 12 is 98~100 millimeters；Outer shroud 11 madial wall with
Multiple guide vanes 13 are connected between the lateral wall of inner disc 12, multiple guide vanes 13 are circumferentially spaced to be set；In inner disc 12
Annular web 14 is provided with surrounded cavity, the outward flange of the annular web 14 is fixedly connected with the madial wall of inner disc 12, inside
The central through hole of disk 12 is provided with boss, in the present embodiment, the external diameter E of annular web 14 close to the side of annular installation portion 112
For 95~98 millimeters, i.e. the diameter F of the internal diameter central through hole of annular web 14 is 47~49 millimeters, preferably 48.2 millis
Rice.
Outer shroud 11 outer shroud cylinder 111 be used for high-speed gas are discharged in jet pipe, the annular installation portion 112 of outer shroud 11 with
Engine housing is fixedly connected, because the external diameter of annular installation portion 112 is more than the external diameter of outer shroud cylinder 111, transition part 114 and annular
The junction of installation portion 112, the curved shape in junction of transition part 114 and outer shroud cylinder 111, outer shroud 11 inner peripheral surface with it is interior
Formed between the outer circumference surface of disk 12 by bending to arcuate furrow radially vertically, in outer shroud 1l inner peripheral surface and inner disc
The air inlet of guider is formed between the end of 12 outer circumference surface；Guide vane 13 be fixedly connected on the madial wall of outer shroud 11 with
Between the lateral wall of inner disc 12, at the position of arcuate furrow, being formed between the outer shroud cylinder 111 and inner disc 12 of outer shroud 11 is used for
The cavity of turbine rotor is installed.
The high temperature and high pressure gas sprayed from combustion chamber are entered between the outer shroud 11 of guider and inner disc 12 from the air inlet
Cavity in, after gas is axially entered at arcuate furrow, by arcuate furrow guide effect occur deflecting, from radially
It is flowed into the cavity of guider.The guide vane 13 being arranged in arcuate furrow plays further guide effect, directing vane
The direction of piece 13 and the direction of the turbo blade for the turbine rotor being arranged in the cavity of guider match so that gas can
Region between the happy turbo blade that turbine rotor is reached by arcuate furrow.Arcuate furrow and guide vane 13 are except can be with
Outside being oriented to the high temperature and high pressure gas discharged from combustion chamber, the high temperature and high pressure gas can also be carried out to decompression processing, and
So that the speed of gas is improved.The physical dimension and position and attitude of guide vane 13 are served certainly to the performance of guider
Qualitatively influence, in the present embodiment, the angle between guide vane 13 and the radial direction of inner disc 12 is 65~70 degree, preferably 70
Degree, it is demonstrated experimentally that can greatly be improved when the angle between guide vane 13 and the radial direction of inner disc 12 is in the number range
The overall thrust performance of engine.In addition, the sum of guide vane 13 is preferably 24, guide vane 13 is in outer shroud 11 and inner disc
Length between 12 outward flanges is preferably 21~23 millimeters, and the thickness of each guide vane 13 is preferably 1~3 millimeter.
The central through hole of inner disc 12 is used for through whirlpool axle, is used to connect bearing in the circumferentially disposed boss 15 of central through hole
Room, the bearing chamber that can be directed to device with being arranged in front of guider using the boss 15 is fixed together, in the present embodiment,
Boss 15 is provided with two, the both sides of corresponding centrally disposed through hole, and the size of boss 15 is 3 × 3 millimeters, certainly, boss
15 can also be provided with more, divide equally setting along the circumference of central through hole.
Because guider in the front of miniature turbine jet engines undergos the impact of warm gases at high pressure, so to being oriented to
The structural strength and heat-proof quality of device have compared with strict requirements, and annular web 14, annular are provided with the central through hole of inner disc 12
Entity is formed between web 14 and inner disc 12, Cooling Holes 141 are provided with annular web 14, between annular web 14 and inner disc 12
Entity connection can not only greatly improve the structural strength of guider, additionally it is possible to play heat-insulated effect, and Cooling Holes 141 equally have
There is enhancing air circulation effect, the jet pipe that can so prevent from being located at turbine rotor and rear portion inside guider was heated
Greatly.
The annular installation portion 112 of the outer shroud 11 of the utility model guider is directly fixedly connected with engine housing, inside
The central through hole of disk 12 is provided with boss close to the side of annular installation portion 112, fixed to connect for being fixedly connected with and positioning bearing chamber
Connect and position very convenient, inner disc 12, which is surrounded, is provided with annular web 14, shape between annular web 14 and inner disc 12 in cavity
The structural strength of guider can not only be greatly improved into entity connection, additionally it is possible to played heat-insulated effect, can be prevented from being located at
The jet pipe of turbine rotor and rear portion inside guider is heated excessive, it is possible to increase miniature turbine jet engines thrust
Energy.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
Any modifications, equivalent substitutions and improvements made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (9)
1. a kind of guider, including outer shroud, inner disc and it is fixedly connected with guide vane therebetween, it is characterised in that institute
State outer shroud and annular installation portion is set including outer shroud cylinder, with outer shroud cylinder coaxial line, in the annular installation portion and the outer shroud
Transition part is connected between cylinder, it is circumferentially spaced on the side wall of the annular installation portion to be provided with several outer shroud connecting holes；
The inner disc is cylindrical in shape, the inner disc surround in cavity be provided with annular web, the outward flange of the annular web with it is described
The madial wall of inner disc is fixedly connected, the inner disc central through hole close to the side of the annular installation portion be provided with boss.
2. guider according to claim 1, it is characterised in that the boss be provided with it is multiple, along along the inner disc
The circumference of heart through hole divides equally setting.
3. guider according to claim 2, it is characterised in that the boss is provided with two, corresponding to be arranged on institute
State the both sides of the central through hole of inner disc.
4. guider according to claim 1, it is characterised in that the external diameter of the annular installation portion of the outer shroud is 185~
190 millimeters, internal diameter is 183~185 millimeters, and the internal diameter of the outer shroud cylinder is 145~147 millimeters, and the external diameter of the inner disc is 98
~100 millimeters, the external diameter of the annular web is 95~98 millimeters, a diameter of the 47~49 of the central through hole of the annular web
Millimeter.
5. guider according to claim 4, it is characterised in that the internal diameter of the outer shroud is 184 millimeters, the outer shroud cylinder
Internal diameter be 146 millimeters, a diameter of 48.2 millimeters of the central through hole of the annular web.
6. guider according to claim 1, it is characterised in that the outer shroud connecting hole is provided with four, along the ring
The circumference of shape installation portion divides equally setting, and its aperture is 4 millimeters.
7. guider according to claim 1, it is characterised in that the folder between the guide vane and the inner disc radial direction
Angle is 65~70 degree.
8. guider according to claim 1, it is characterised in that the guide vane is 24.
9. guider according to claim 1, it is characterised in that the thickness of each guide vane is 1~3 millimeter,
Length of the guide vane between the outer shroud and the inner disc outward flange is 21~23 millimeters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621492763.3U CN206352530U (en) | 2016-12-30 | 2016-12-30 | A kind of guider |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621492763.3U CN206352530U (en) | 2016-12-30 | 2016-12-30 | A kind of guider |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206352530U true CN206352530U (en) | 2017-07-25 |
Family
ID=59349288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621492763.3U Active CN206352530U (en) | 2016-12-30 | 2016-12-30 | A kind of guider |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206352530U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
-
2016
- 2016-12-30 CN CN201621492763.3U patent/CN206352530U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN110617115B (en) * | 2019-10-29 | 2021-11-02 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
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