CN205089456U - Centrifugal turbine engine - Google Patents
Centrifugal turbine engine Download PDFInfo
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- CN205089456U CN205089456U CN201520809234.0U CN201520809234U CN205089456U CN 205089456 U CN205089456 U CN 205089456U CN 201520809234 U CN201520809234 U CN 201520809234U CN 205089456 U CN205089456 U CN 205089456U
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Abstract
The utility model relates to a centrifugal turbine engine, including shell, compressor, combustion chamber, turbine, the compressor constitutes by stator blade group and rotor blade, stator blade group and rotor blade group being has at least two -layer blades by outside impartial distribution of ab intra on the inboard circumferencial direction, stator blade group organizes with rotor blade and is the mutual multistage overall arrangement that interlocks the distribution, the utility model discloses utilizing the combination overall arrangement of a stator impeller assembly and a rotor impeller assembly, having realized multistagely on the circumferencial direction concatenating the compression, make the single -stage pressure boost relative altitude of its existing centrifugal blade of calming the anger, have the advantage that axial compressor can the multi -stage series connection pressure boost again, it also has simple structure in addition, and is small, make lower, the difficult advantage of surging of taking place of technical requirement.
Description
Technical field
The utility model relates to a kind of turbogenerator, particularly the centrifugal turbogenerator of one.
Background technique
Turbogenerator with gas compressor is divided into axial flow and centrifugal two kinds by its mode difference of calming the anger, and the compressor of axial-flow engine has many blades, the similar propeller blade of shape, but is divided into " stator " and " rotor " two kinds.Rotor usually rotates just as propeller cavitation, in the process rotated by air-flow to pusher, at this moment the pressure of air-flow will improve, and temperature also can raise.The function of stator is guided back axially by the air-flow producing rotation because of the effect of rotor, enters next group rotor with correct angle.Normally a group rotor and one group of stator configure alternately, and a group rotor and stator are just called one-level.Axial-flow compressor volume is comparatively large, and single stage supercharging is more centrifugal low, easy surge, but plural serial stage behind efficiency is high, shortcoming be easily occur surge, manufacturing process harsh, involve great expense.
The centrifugal force that the compressor of centrifugal engine produces when being then and utilizing vane rotary outwards pushes air-flow to casing, and produces the effect of pressurization.The single stage supercharging of centrifugal-flow compressor is than high, the centrifugal compressor of one-level just can have the compression ratio of several grades of Axial Flow Compressors, centrifugal jet engine structure is simple, volume is little, technical requirements is lower, the advantage of surge not easily occurs, but not easily multi-stage serial connection thus the total pressure ratio of influential system, efficiency is lower, is commonly used on the first order of turboshaft engine and the auxiliary power unit of airline carriers of passengers.
Summary of the invention
For the deficiencies in the prior art, the utility model provides a kind of and had both had the advantage that centrifugal engine structure is simple, volume is little, manufacturing technology requirement is lower, surge not easily occurs, what have again axial-flow engine can improve the total pressure ratio of system, the centrifugal turbogenerator of one of the advantage that efficiency is high by plural serial stage.
The technical solution of the utility model is achieved in that a kind of centrifugal turbogenerator, comprise shell, gas compressor, firing chamber, turbine, described gas compressor is made up of stator blade group and rotor blade group, described stator blade group and rotor blade group all for by inside circumference direction from inside to outside equal distribution be made up of at least two-layer blade.
The circular ring that described stator blade and rotor blade every layer are all made up of multiple sheet blade,
The angle of attack direction of described stator blade and the blade of rotor blade is contrary,
Described stator blade group and rotor blade group are the multistage layout of interlaced distribution, by one deck stator blade that inside circumference direction distributes from inside to outside, shell adds that compressor rotor is considered as one-level by one deck rotor blade that inside circumference direction distributes from inside to outside calms the anger blade, described gas compressor has at least two-stage to calm the anger blade.
Described stator blade and rotor blade from motor axle center to circumferencial direction blade lateral length in successively successively decreasing.
The utility model has following good effect: first the present invention composite configuration of a stator impeller sets and an impeller of rotor group, achieve circumferentially multi-stage serial connection compression, make the single stage supercharging of its existing centrifugal blade of calming the anger than high, there is again the advantage of Axial Flow Compressor energy plural serial stage supercharging, and it also has structure simple, volume is little, manufacturing technology requires the advantage lower, surge not easily occurs.
Accompanying drawing explanation
Fig. 1 is one of structural representation of the present utility model.
Fig. 2 is rotor blade group structural representation of the present utility model.
Fig. 3 is stator blade group structural representation of the present utility model
In figure: calm the anger blade, 3 rotors of 1 shell, 2 stators are calmed the anger blade, 4 running shafts, 5 firing chambers, 6 oil pipe 7 rotor scroll, 8 stator turbines, 9 bearings
Embodiment
As shown in Figure 1, 2, 3, a kind of centrifugal turbogenerator, comprise shell 1 and be positioned at shell 1 and with the running shaft 4 of shell 1 by bearing 9 active link, described shell 1 internal fixtion be provided with the stator being positioned at its interior front calm the anger vane group 2, be positioned at the firing chamber 5 inside shell 1 and be positioned at the stator turbine 8 of shell 1 posterior medial, be provided with oil pipe 6 in described firing chamber 5.
On described running shaft 4, its front portion is fixedly installed calm the anger vane group 3, rear portion of rotor and is fixedly installed rotor scroll 7.
Described stator blade group 2 and rotor blade group 3 all for by inside circumference direction from inside to outside the two-layer blade of equal distribution form, the circular ring of the stator blade in described stator blade group 2 and rotor blade group 3 and rotor blade at least 5 every layer sheet blades compositions.
Described stator blade and rotor blade successively successively decrease to circumferencial direction length of blade journey from motor axle center, the angle of attack direction of described stator blade group 2 and the blade of rotor blade group 3 is contrary, and the blade of stator blade group 2 and rotor blade group 3 is interspersed respectively on the inner side of shell 1 and running shaft 4.
One deck rotor blade that one deck stator blade on described shell adds on running shaft 4 is considered as one-level and calms the anger blade, described blade of calming the anger has at least two-stage to calm the anger blade, be that the first order is calmed the anger blade near one deck stator blade of running shaft 4 and rotor blade, another layer of stator blade of circumferencial direction and rotor blade are calm the anger blade in the second level.
The utility model is when carrying out practically, gas gets rid of to first order stator blade via the first order rotor blade of High Rotation Speed to gas by gas, the air-flow of High Rotation Speed enters into the rightabout stator blade of angle, slow down in the flow rotation direction that stator blade makes to produce High Rotation Speed because of the effect of rotor blade or stop and part kinetic energy become pressure energy, another part kinetic energy can become centrifugal potential energy because of the reason that stator blade angle is contrary with rotor blade, such air-flow had both added pressure and had accelerated centrifugal speed, also make the rotation of air-flow slow down or stop simultaneously, be more conducive to the potential energy that next stage rotor blade is rotating when entering next stage rotor blade be like this applied on air-flow.Simultaneously also because stator blade and rotor blade successively successively decrease to circumferencial direction length of blade journey from motor axle center, successively decrease step by step in its space also journey, gas is accelerated to be thrown in the small space at the edge of compressor through each grade blade centrifugal force by a large amount of gases in the large space of center, the pressure energy that its kinetic energy finally becomes, so accelerate through the pressurization of multi-stage booster blade, multistage pressure superposes the compression that increases progressively and final very high pressure enters firing chamber 5, simultaneously fuel oil sprays the oil plant of atomization by the oil nozzle of oil pipe 6 to firing chamber 5 and high-pressure air and mist of oil mixed gas is lighted with high-pressure air mixed firing device, mixture combustion expands, drive rotor turbine 7 rotates, the rotor scroll 7 rotated drives the rotor blade group 3 of gas compressor to rotate, air-flow is after worm gear, from puff prot ejection work done.
Claims (2)
1. a centrifugal turbogenerator, comprises shell, gas compressor, firing chamber, turbine, it is characterized in that: described gas compressor is made up of stator blade group and centrifugal rotor vane group,
Described stator blade group and rotor blade group are interlaced distribution,
Described stator blade group and centrifugal rotor vane group all for by circumferentially from inside to outside equal distribution be made up of at least two-layer blade,
The angle of attack direction of described stator blade and the blade of rotor blade is contrary,
The circular ring that described stator blade and rotor blade every layer are all made up of multiple sheet blade,
Described stator blade and rotor blade be all from motor axle center to circumferencial direction blade lateral length in successively successively decreasing.
2. the centrifugal turbogenerator of one according to claim 1, is characterized in that: described stator blade and rotor blade every layer are all the circular rings being at least 5 blade compositions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520809234.0U CN205089456U (en) | 2015-10-12 | 2015-10-12 | Centrifugal turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520809234.0U CN205089456U (en) | 2015-10-12 | 2015-10-12 | Centrifugal turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205089456U true CN205089456U (en) | 2016-03-16 |
Family
ID=55480151
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520809234.0U Expired - Fee Related CN205089456U (en) | 2015-10-12 | 2015-10-12 | Centrifugal turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205089456U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201650A (en) * | 2015-10-12 | 2015-12-30 | 常胜 | Centrifugal turbine engine |
-
2015
- 2015-10-12 CN CN201520809234.0U patent/CN205089456U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201650A (en) * | 2015-10-12 | 2015-12-30 | 常胜 | Centrifugal turbine engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160316 Termination date: 20171012 |