CN103382856A - Housing movable vane wheel mechanism - Google Patents
Housing movable vane wheel mechanism Download PDFInfo
- Publication number
- CN103382856A CN103382856A CN2013102887763A CN201310288776A CN103382856A CN 103382856 A CN103382856 A CN 103382856A CN 2013102887763 A CN2013102887763 A CN 2013102887763A CN 201310288776 A CN201310288776 A CN 201310288776A CN 103382856 A CN103382856 A CN 103382856A
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- Prior art keywords
- channel body
- rotating channel
- movable vane
- wheel mechanism
- reach
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- 238000010304 firing Methods 0.000 description 8
- 239000000446 fuel Substances 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000008093 supporting effect Effects 0.000 description 1
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Abstract
The invention discloses a housing movable vane wheel mechanism which comprises a rotating passage body and a loaded axle, wherein the loaded axle is arranged in the rotating passage body; movable vanes are arranged on the inner wall of the rotating passage body; reversed movable vanes are arranged on the loaded axle; the reversed movable vanes are matched with the movable vanes; a bearing is mounted on the loaded axle; the rotating passage body is in rotational connection with the loaded axle through a support body and the bearing. The housing movable vane wheel mechanism has high efficiency and power density, and has a high thrust-weight ratio when used as a jet engine.
Description
Technical field
The present invention relates to heat energy and power, particularly shell movable vane wheel mechanism.
Background technique
Up to now, no matter be aeroengine or gas turbine, be all interior axle reaches the movable vane rotation that is connected with interior axle, shell reaches the stator blade that is connected with shell and remains static.This structure can not be utilized the centrifugal force of rotary component generation, has therefore affected the efficient of gas compressor and turbine.Therefore need a kind of novel impeller of invention mechanism.
Summary of the invention
In order to solve above-mentioned problems of the prior art, the technological scheme that the present invention proposes is as follows:
A kind of shell movable vane wheel mechanism, comprise rotating channel body and reach, described reach is arranged in described rotating channel body, on described rotating channel body inwall, movable vane is set, establish reverse movable vane on described reach, described reverse movable vane and described movable vane match, and establish bearing on described reach, and described rotating channel body is rotationally connected through described bearing and described reach through support again.
On described rotating channel body, the power input structure is set, the reverse power input structure is set on described reach.
Described rotating channel body is made as convergent rotating channel body.
Described rotating channel body is made as flaring rotating channel body.
Described rotating channel body is made as convergent flaring rotating channel body, establishes the firing chamber in described convergent flaring rotating channel body.
Described firing chamber is located in the confluence of the converging transition of described convergent flaring rotating channel body and gradually expanding section.
Establish power output structure on described convergent flaring rotating channel body, establish the reverse power export structure on described reach.
Establish propeller cavitation on described convergent flaring rotating channel body, establish counter rotating propeller on described reach.
Fan on described convergent flaring rotating channel body is established reverse fan on described reach.
In the above-mentioned structure that is provided with described convergent flaring rotating channel body, can establish the fuel channel that is communicated with described firing chamber in described reach.
Principle of the present invention is: the rotation by described rotating channel body produces centrifugal force, utilize this centrifugal force that the gas density in described rotating channel body is increased, thereby improve described movable vane and the interactional efficient of described reverse movable vane, and then improve compression efficiency and expansion mechanical efficiency.
In the present invention, so-called " rotating channel body " refers to the housing that can rotate, such as tubbiness housing, convergent housing, flaring housing etc.
In the present invention, so-called " convergent " refers to dwindle gradually by the fluid flow direction channel cross-section.
In the present invention, so-called " flaring " refers to enlarge gradually by the fluid flow direction channel cross-section.
In the present invention, so-called " power input structure " refers to receive the structure of power, such as the gear that receives power, belt pulley, rotatingshaft link etc.So-called " reverse power input structure " refers to receive the structure of the power opposite with the sense of rotation of above-mentioned power, its objective is and make described rotating channel body and the rotation of described reach oppositely on the contrary, such as the gear that receives power, belt pulley, rotatingshaft link etc.
In the present invention, so-called " power output structure " refers to the structure of outputting power, such as the gear of outputting power, belt pulley, rotatingshaft link etc.So-called " reverse power export structure " refers to export the structure of the power opposite with the sense of rotation of above-mentioned power, its objective is to make the opposite described rotating channel body of sense of rotation and described reach external outputting power simultaneously such as the gear of outputting power, belt pulley, rotatingshaft link etc.
In the present invention, described propeller cavitation is opposite with described counter rotating propeller sense of rotation, but thrust direction is identical.
In the present invention, described fan is opposite with described reverse fan sense of rotation, but thrust direction is identical.
In the present invention, described support is to be connected with described rotating channel body, the link that is rotationally connected through described bearing and described reach.Described support is not only born the supporting effect between described rotating channel body and described reach, also will have the fluid passage, and gas can be flowed in described rotating channel.
In the present invention, so-called " reach " refers to carry the reach that self rotates that described rotating channel body is rotatably connected with body, and its inside can arrange fuel channel, signalling channel etc., the reach that for example is rotatably connected with body.
In " shell movable vane wheel mechanism " disclosed in this invention, due to described rotating channel body and the described movable vane integral-rotation that is connected thereof, so described movable vane is the centrifugal action on the Tensile direction not when rotated, but the effect of the power on direction by compression, and strong effect all is summed up as the effect to described rotating channel body, and a little less than described rotating channel body is subjected to spatial constraints, and operating temperature is low, therefore its intensity can be in higher state, therefore can improve the rotating speed of described rotating channel body, and then raise the efficiency.
In the present invention, should according to the known technology in motor, heat engine and heat power field, necessary parts, unit or system be set in the place of necessity.
Beneficial effect of the present invention is as follows: efficient of the present invention is high, and specific power is high, and when using as jet engine, thrust weight ratio is high.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the present invention 1;
Fig. 2 is the structural representation of the embodiment of the present invention 2;
Fig. 3 is the structural representation of the embodiment of the present invention 3;
Fig. 4 is the structural representation of the embodiment of the present invention 4,
Fig. 5 is the structural representation of the embodiment of the present invention 5;
Fig. 6 is the structural representation of the embodiment of the present invention 6;
Fig. 7 is the structural representation of the embodiment of the present invention 7;
Fig. 8 is the structural representation of the embodiment of the present invention 8;
In figure:
1 reach, 12 supports, 2 movable vanes, 3 reverse movable vanes, 4 bearings, 5 power input structures, 55 reverse power input structures, 6 firing chambers, 61 fuel channels, 7 power output structures, 77 reverse power export structures, 8 propeller cavitations, 88 counter rotating propellers, 9 fans, 99 reverse fans, 101 convergent rotating channel bodies, 102 flaring rotating channel bodies, 100 convergent flaring rotating channel bodies.
Embodiment
Shell movable vane wheel mechanism as shown in Figure 1, comprise rotating channel body and reach 1, described rotating channel body is made as convergent rotating channel body 101, described reach 1 is arranged in described convergent rotating channel body 101, on described convergent rotating channel body 101 inwalls, movable vane 2 is set, establish reverse movable vane 3 on described reach 1, described reverse movable vane 3 and described movable vane 2 match, establish bearing 4 on described reach 1, described convergent rotating channel body 101 is rotationally connected with described reach 1 through described bearing 4 through support 12 again.
As mode of execution that can conversion, described rotating channel body can be made as other shapes that are fit to such as tubbiness.
When the described shell movable vane wheel mechanism of the present embodiment was worked, the sense of rotation of described rotating channel body and described reach 1 was opposite.
Shell movable vane wheel mechanism as shown in Figure 2, it is on embodiment 1 basis:
Set up power input structure 5 on described convergent rotating channel body 101, set up reverse power input structure 55 on described reach 1.The described shell movable vane wheel mechanism of the present embodiment consists of gas compressor.
Shell movable vane wheel mechanism as shown in Figure 3, itself and embodiment's 1 difference part is:
Described rotating channel structural reform is established flaring rotating channel body 102.
Shell movable vane wheel mechanism as shown in Figure 4, it is on embodiment 3 basis:
Establish power output structure 7 on described flaring rotating channel body 102, establish reverse power export structure 77 on described reach 1.Described shell movable vane wheel mechanism in the present embodiment consists of turbine.
Embodiment 5
Shell movable vane wheel mechanism as shown in Figure 5, itself and embodiment's 1 difference part is:
Described rotating channel structural reform is established convergent flaring rotating channel body 100, establish firing chamber 6 in described convergent flaring rotating channel body 100, described firing chamber 6 is located in the confluence of the converging transition of described convergent flaring rotating channel body 100 and gradually expanding section, establishes the fuel channel 61 that is communicated with described firing chamber 6 in described reach 1.
Described shell movable vane wheel mechanism in the present embodiment consists of jet engine.
Shell movable vane wheel mechanism as shown in Figure 6, it is on embodiment 5 basis:
Set up power output structure 7 on described convergent flaring rotating channel body 100, set up reverse power export structure 77 on described reach 1.Described shell movable vane wheel mechanism in the present embodiment can consist of gas turbine.
Shell movable vane wheel mechanism as shown in Figure 7, it is on embodiment 5 basis:
Set up propeller cavitation 8 on described convergent flaring rotating channel body 100, set up counter rotating propeller 88 on described reach 1.Described shell movable vane wheel mechanism in the present embodiment consists of turbo oar engine.
Shell movable vane wheel mechanism as shown in Figure 8, it is on embodiment 5 basis:
Set up fan 9 on described convergent flaring rotating channel body 100, set up reverse fan 99 on described reach 1.Described shell movable vane wheel mechanism in the present embodiment consists of turbofan engine.
As mode of execution that can conversion, in embodiment 5 to 8, described firing chamber 6 can change other places that are arranged in described convergent flaring rotating channel body 100 into.
As mode of execution that can conversion, in embodiment 5 to 8, described fuel channel 61 can be located in described reach 1, and is provided in a side of other places, such as being arranged on described convergent flaring rotating channel body 100.
Obviously, the invention is not restricted to above embodiment, according to known technology and the technological scheme disclosed in this invention of related domain, can derive or association goes out many flexible programs, all these flexible programs also should be thought protection scope of the present invention.
Claims (10)
1. shell movable vane wheel mechanism, comprise rotating channel body and reach (1), it is characterized in that: described reach (1) is arranged in described rotating channel body, movable vane (2) is set on the inwall of described rotating channel body, establish reverse movable vane (3) on described reach (1), described reverse movable vane (3) and described movable vane (2) match, establish bearing (4) on described reach (1), described rotating channel body is rotationally connected through described bearing (4) and described reach (1) through support (12) again.
2. shell movable vane wheel mechanism as claimed in claim 1, is characterized in that: power input structure (5) is set on described rotating channel body, reverse power input structure (55) is set on described reach (1).
3. shell movable vane wheel mechanism as claimed in claim 1 or 2, it is characterized in that: described rotating channel body is made as convergent rotating channel body (101).
4. shell movable vane wheel mechanism as claimed in claim 1 or 2, it is characterized in that: described rotating channel body is made as flaring rotating channel body (102).
5. as shell movable vane wheel mechanism as described in claim 1 or 4, it is characterized in that: establish power input structure (7) on described flaring rotating channel body (102), establish reverse power input structure (77) on described reach (1).
6. shell movable vane wheel mechanism as claimed in claim 1, it is characterized in that: described rotating channel body is made as convergent flaring rotating channel body (100), establishes firing chamber (6) in described convergent flaring rotating channel body (100).
7. shell movable vane wheel mechanism as claimed in claim 6 is characterized in that: described firing chamber (6) are located in the confluence of the converging transition of described convergent flaring rotating channel body (100) and gradually expanding section.
8. as shell movable vane wheel mechanism as described in claim 6 or 7, it is characterized in that: establish power output structure (7) on described convergent flaring rotating channel body (100), establish reverse power export structure (77) on described reach (1).
9. as shell movable vane wheel mechanism as described in claim 6 or 7, it is characterized in that: establish propeller cavitation (8) on described convergent flaring rotating channel body (100), establish counter rotating propeller (88) on described reach (1).
10. as shell movable vane wheel mechanism as described in claim 6 or 7, it is characterized in that: establish fan (9) on described convergent flaring rotating channel body (100), establish reverse fan (99) on described reach (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102887763A CN103382856A (en) | 2012-08-25 | 2013-07-10 | Housing movable vane wheel mechanism |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210307223 | 2012-08-25 | ||
| CN201210307223.3 | 2012-08-25 | ||
| CN2013102887763A CN103382856A (en) | 2012-08-25 | 2013-07-10 | Housing movable vane wheel mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103382856A true CN103382856A (en) | 2013-11-06 |
Family
ID=49490760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013102887763A Pending CN103382856A (en) | 2012-08-25 | 2013-07-10 | Housing movable vane wheel mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103382856A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015021522A1 (en) * | 2013-08-16 | 2015-02-19 | Milani Paulo Giacomo | Axial turbomachines with rotary housing and fixed central element |
| WO2016050006A1 (en) * | 2014-09-29 | 2016-04-07 | 摩尔动力(北京)技术股份有限公司 | Compression-expansion counter-rotating impeller mechanism |
| WO2016127731A1 (en) * | 2015-02-15 | 2016-08-18 | 靳北彪 | Inter-pressure impeller mechanism |
| CN106907180A (en) * | 2015-12-09 | 2017-06-30 | 熵零技术逻辑工程院集团股份有限公司 | Contra-rotating rotor mechanism |
| CN111412063A (en) * | 2020-03-26 | 2020-07-14 | 夏前锦 | Novel drum type gas turbine |
| CN112879158A (en) * | 2020-12-19 | 2021-06-01 | 李智蕾 | Combustion chamber housing rotary aircraft engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03217601A (en) * | 1990-01-22 | 1991-09-25 | Hiroyasu Tanigawa | Steam turbine of all moving blade |
| US5079916A (en) * | 1982-11-01 | 1992-01-14 | General Electric Company | Counter rotation power turbine |
| JPH04237801A (en) * | 1991-01-17 | 1992-08-26 | Mitsubishi Heavy Ind Ltd | Two-shaft contrarotating axial turbine |
| CN2177811Y (en) * | 1993-07-21 | 1994-09-21 | 张士维 | Turbine |
| CN1662734A (en) * | 2002-06-26 | 2005-08-31 | R－喷射器工程有限公司 | Orbiting combustion nozzle engine |
| EP1614855A1 (en) * | 2004-07-05 | 2006-01-11 | Siemens Aktiengesellschaft | Turbomachine and method to operate such a turbomachine |
-
2013
- 2013-07-10 CN CN2013102887763A patent/CN103382856A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5079916A (en) * | 1982-11-01 | 1992-01-14 | General Electric Company | Counter rotation power turbine |
| JPH03217601A (en) * | 1990-01-22 | 1991-09-25 | Hiroyasu Tanigawa | Steam turbine of all moving blade |
| JPH04237801A (en) * | 1991-01-17 | 1992-08-26 | Mitsubishi Heavy Ind Ltd | Two-shaft contrarotating axial turbine |
| CN2177811Y (en) * | 1993-07-21 | 1994-09-21 | 张士维 | Turbine |
| CN1662734A (en) * | 2002-06-26 | 2005-08-31 | R－喷射器工程有限公司 | Orbiting combustion nozzle engine |
| EP1614855A1 (en) * | 2004-07-05 | 2006-01-11 | Siemens Aktiengesellschaft | Turbomachine and method to operate such a turbomachine |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015021522A1 (en) * | 2013-08-16 | 2015-02-19 | Milani Paulo Giacomo | Axial turbomachines with rotary housing and fixed central element |
| WO2016050006A1 (en) * | 2014-09-29 | 2016-04-07 | 摩尔动力(北京)技术股份有限公司 | Compression-expansion counter-rotating impeller mechanism |
| WO2016127731A1 (en) * | 2015-02-15 | 2016-08-18 | 靳北彪 | Inter-pressure impeller mechanism |
| CN106907180A (en) * | 2015-12-09 | 2017-06-30 | 熵零技术逻辑工程院集团股份有限公司 | Contra-rotating rotor mechanism |
| CN111412063A (en) * | 2020-03-26 | 2020-07-14 | 夏前锦 | Novel drum type gas turbine |
| CN112879158A (en) * | 2020-12-19 | 2021-06-01 | 李智蕾 | Combustion chamber housing rotary aircraft engine |
| CN112879158B (en) * | 2020-12-19 | 2022-04-01 | 李智蕾 | Combustion chamber housing rotary aircraft engine |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20131106 |