CN205779266U - The actuating device of turbojet engine - Google Patents
The actuating device of turbojet engine Download PDFInfo
- Publication number
- CN205779266U CN205779266U CN201620453670.3U CN201620453670U CN205779266U CN 205779266 U CN205779266 U CN 205779266U CN 201620453670 U CN201620453670 U CN 201620453670U CN 205779266 U CN205779266 U CN 205779266U
- Authority
- CN
- China
- Prior art keywords
- bearing
- turbojet engine
- central siphon
- main shaft
- actuating device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000012856 packing Methods 0.000 claims abstract description 9
- 239000000919 ceramic Substances 0.000 claims description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 238000005299 abrasion Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 8
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
Landscapes
- Rolling Contact Bearings (AREA)
Abstract
The utility model discloses the actuating device of a kind of turbojet engine, including: central siphon；One main shaft is set in described central siphon；One end of described main shaft is provided with turbine；It is installed on inside described turbine and inserts the bearing of described main shaft；It is characterized in that, also include: the turbine packing ring being arranged between described bearing and described shaft tube inner wall；The outside of described central siphon is provided with heat shield；It is arranged at the projection on described heat shield；It is positioned at the nozzle ring of described protruding side.This utility model is not only simple in structure, reasonable in design, and reduce the phenomenons such as abrasion that Bearing Temperature causes, fatigue flake, fracture, it is ensured that turbojet engine properly functioning.
Description
Technical field
This utility model relates to turbojet engine technical field, the transmission of a kind of turbojet engine
Device.
Background technology
Micro Turbine Jet Engine has obtained as aircraft power plant paying close attention to widely the most at home.Its highest turn
Scooter (10～16) × 104r/min.The centrifugal force of high speed conditions lower bearing steel ball increases rapidly so that steel ball and raceway groove
It is susceptible to contact fatigue damage.The increase of gyroscopic couple makes steel ball and raceway groove generation sliding friction, contact area local temperature rise
Too high, cause lubrication failure generation surface abrasion.Thus in the environment of high speed, high temperature, easily there is excessive wear, raceway in bearing
Burn, heat lose phenomenons such as killing, have had a strong impact on the properly functioning of turbojet engine.
Therefore, the actuating device how providing a kind of turbojet engine is the problem that those skilled in the art need solution badly.
Utility model content
In view of this, this utility model provides the actuating device of a kind of turbojet engine, by arranging inside bearing
There is turbine packing ring and heat shield is set outside central siphon, under not affecting the overall structure of bearing, intensity and work premise,
The temperature of bearing can be effectively reduced, it is ensured that the normal work of turbojet engine.
In order to achieve the above object, this utility model adopts the following technical scheme that
A kind of actuating device of turbojet engine, including: central siphon；One main shaft is set in described central siphon；The one of described main shaft
End is provided with turbine；It is installed on inside described turbine and inserts the bearing of described main shaft；Also include: be arranged at described bearing and institute
State the turbine packing ring between shaft tube inner wall；The outside of described central siphon is provided with heat shield；It is arranged at the projection on described heat shield；
It is positioned at the nozzle ring of described protruding side.
Preferably, in the actuating device of above-mentioned turbojet engine, described central siphon uses aluminium material, serves support and leads
To effect.
Preferably, in the actuating device of above-mentioned turbojet engine, described main shaft entirety is stepped, uses stainless steel
Matter, and it is provided with left hand thread at the two ends of described main shaft.
Preferably, in the actuating device of above-mentioned turbojet engine, described turbine packing ring is provided with two.
Preferably, in the actuating device of above-mentioned turbojet engine, described bearing is by inner ring, is arranged at outside described inner ring
The Ceramic Balls of side and be positioned at outer ring composition outside described Ceramic Balls, and described bearing is provided with two, the most described
Bearing uses high-temperature ceramics ball bearing to make.
Preferably, in the actuating device of above-mentioned turbojet engine, described nozzle ring is irregular.
Understanding via above-mentioned technical scheme, compared with prior art, this utility model is open provides the eruption of a kind of whirlpool
The actuating device of motivation, turbojet engine produces high-temperature high-pressure fuel gas from combustor and flows backwards through high-temperature turbine, can be in part
Turbine expands and is converted into mechanical energy, drive turbine to rotate, the rotation having rotarily driven main shaft of turbine.At turbojet engine
In work process, bearing not only affects main shaft critical speed position, and in high temperature, the reliability of environment under high pressure lower bearing and longevity
Life determines reliability and the life-span of turbojet engine.This utility model adds turbine pad between bearing and shaft tube inner wall
Circle, reduces the vibration of main shaft, maintains the stability of main shaft work.The outside of central siphon is provided with heat shield, decrease from
The high temperature of combustor penetrates in central siphon, reduces the temperature of bearing, further ensures the properly functioning of turbojet engine.
Accompanying drawing explanation
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, the accompanying drawing in describing below is only
It is embodiment of the present utility model, for those of ordinary skill in the art, on the premise of not paying creative work, also
Other accompanying drawing can be obtained according to the accompanying drawing provided.
Fig. 1 accompanying drawing is structural representation of the present utility model.
In FIG:
1 be central siphon, 2 be main shaft, 3 be bearing, 4 be turbine packing ring, 5 be heat shield, 6 for protruding, 7 be nozzle ring.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not under making creative work premise
The every other embodiment obtained, broadly falls into the scope of this utility model protection.
This utility model embodiment discloses the actuating device of a kind of turbojet engine, the letter of this utility model not only structure
Single, reasonable in design, and reduce the phenomenons such as abrasion that Bearing Temperature causes, fatigue flake, fracture, it is ensured that whirlpool is erupted
Motivation properly functioning.
A kind of actuating device of turbojet engine, including: central siphon 1；One main shaft 2 is set in central siphon 1；One end of main shaft 2 sets
It is equipped with turbine；It is installed on inside turbine and inserts the bearing 3 of main shaft 2；Also include: be arranged between bearing 3 and central siphon 1 inwall
Turbine packing ring 4；The outside of central siphon 1 is provided with heat shield 5；The projection 6 being arranged on heat shield 5；It is positioned at the nozzle of protruding 6 sides
Ring 7.
In order to optimize technique scheme further, central siphon 1 uses aluminium material, serves the effect supporting and guiding.
In order to optimize technique scheme further, main shaft 2 is overall stepped, uses stainless steel, and is leading
The two ends of axle 2 are provided with left hand thread.
In order to optimize technique scheme further, turbine packing ring 4 is provided with two.
In order to optimize technique scheme further, bearing 3 is by inner ring, is arranged at the Ceramic Balls outside inner ring and position
Outer ring outside Ceramic Balls forms, and bearing 3 is provided with two, and bearing 3 uses high-temperature ceramics ball bearing to make simultaneously
's.
In order to optimize technique scheme further, nozzle ring 7 is in irregular.
In this specification, each embodiment uses the mode gone forward one by one to describe, and what each embodiment stressed is and other
The difference of embodiment, between each embodiment, identical similar portion sees mutually.For device disclosed in embodiment
For, owing to it corresponds to the method disclosed in Example, so describe is fairly simple, relevant part sees method part and says
Bright.
Described above to the disclosed embodiments, makes professional and technical personnel in the field be capable of or uses this practicality new
Type.Multiple amendment to these embodiments will be apparent from for those skilled in the art, is determined herein
The General Principle of justice can realize in the case of without departing from spirit or scope of the present utility model in other embodiments.Cause
This, this utility model is not intended to be limited to the embodiments shown herein, and is to fit to and principles disclosed herein
The widest scope consistent with features of novelty.
Claims (5)
1. an actuating device for turbojet engine, including: central siphon (1)；One main shaft (2) is set in described central siphon (1)；Described master
One end of axle (2) is provided with turbine；It is installed on inside described turbine and inserts the bearing (3) of described main shaft (2)；Its feature exists
In, also include: the turbine packing ring (4) being arranged between described bearing (3) and described central siphon (1) inwall；Outside described central siphon (1)
Side is provided with heat shield (5)；The projection (6) being arranged on described heat shield (5)；It is positioned at the nozzle ring of described projection (6) side
(7)。
The actuating device of turbojet engine the most according to claim 1, it is characterised in that described central siphon (1) uses aluminium
Matter.
The actuating device of turbojet engine the most according to claim 1, it is characterised in that described main shaft (2) is overall in rank
Scalariform, uses stainless steel, and is provided with left hand thread at the two ends of described main shaft (2).
The actuating device of turbojet engine the most according to claim 1, it is characterised in that described turbine packing ring (4) is arranged
There are two.
The actuating device of turbojet engine the most according to claim 1, it is characterised in that described bearing (3) be by inner ring,
It is arranged at the Ceramic Balls outside described inner ring and is positioned at what the outer ring outside described Ceramic Balls formed, and described bearing (3)
Being provided with two, the most described bearing (3) uses high-temperature ceramics ball bearing to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620453670.3U CN205779266U (en) | 2016-05-19 | 2016-05-19 | The actuating device of turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620453670.3U CN205779266U (en) | 2016-05-19 | 2016-05-19 | The actuating device of turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205779266U true CN205779266U (en) | 2016-12-07 |
Family
ID=58120100
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620453670.3U Active CN205779266U (en) | 2016-05-19 | 2016-05-19 | The actuating device of turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205779266U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108453344A (en) * | 2018-04-28 | 2018-08-28 | 河北工业大学 | A kind of device and method to circular ring work piece outer round surface re melting process |
-
2016
- 2016-05-19 CN CN201620453670.3U patent/CN205779266U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108453344A (en) * | 2018-04-28 | 2018-08-28 | 河北工业大学 | A kind of device and method to circular ring work piece outer round surface re melting process |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20171218 Address after: Lianchi Qu Nan Jin Zhuang Cun 071000 Hebei city of Baoding Province Patentee after: BAODING XUANYUN TURBOJET POWER EQUIPMENT R&D CO.,LTD. Address before: 071000 unit 301, No. 4, No. 120, 71 Zhong Road, North City, Baoding City, Hebei Patentee before: Wang Dong |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 66 Jianye East Road, Gaokai District, Baoding City, Hebei Province, 071000 Patentee after: BAODING XUANYUN TURBOJET POWER EQUIPMENT R&D CO.,LTD. Country or region after: China Address before: 071000 Nanjinzhuang Village, Lianchi District, Baoding City, Hebei Province Patentee before: BAODING XUANYUN TURBOJET POWER EQUIPMENT R&D CO.,LTD. Country or region before: China |