CN105422313A - Miniature turbofan engine separate exhausting device with rectifier - Google Patents
Miniature turbofan engine separate exhausting device with rectifier Download PDFInfo
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- CN105422313A CN105422313A CN201510899841.5A CN201510899841A CN105422313A CN 105422313 A CN105422313 A CN 105422313A CN 201510899841 A CN201510899841 A CN 201510899841A CN 105422313 A CN105422313 A CN 105422313A
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- rectifier
- turbofan engine
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- middle casing
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Abstract
The invention discloses a miniature turbofan engine separate exhausting device with a rectifier. The miniature turbofan engine separate exhausting device is located in the position of an exhausting outlet of a miniature turbofan engine and comprises an outer case, a turbine guider case, the rectifier, an intermediate case, an inner spray pipe and a center cone which are sequentially connected. The difference value between the shrinkage angle of the rectifier and the shrinkage angle of the inner spray pipe and the difference value between the shrinkage angle of the rectifier and the shrinkage angle of the rear section of the outer case both range from -5 degrees to 5 degrees. By the adoption of the miniature turbofan engine separate exhausting device, friction loss and viscosity loss caused in the exhausting process of the miniature turbofan engine can be greatly reduced; and in addition, the problem that a thread is difficultly machined on high-temperature alloy is solved, connection is convenient, and the structure is simple and feasible.
Description
Technical field
The present invention relates to microminiature turbofan engine field, particularly relate to a kind of Minitype turbofan engine with rectifier and separate venting gas appliance.
Background technique
Micro Turbine Jet Engine have lightweight, power is large, energy storage density is high, power to weight ratio and thrust weight ratio advantages of higher, at present or minute vehicle small-sized at SUAV, miniature missile, jet model plane etc. is widely used.But its oil consumption rate is higher, and thrust still can not meet the power demand of the aircraft such as the miniature Cruise Missile such as needing the more ammunitions of carry.Reduce oil consumption rate to have great significance to micro-satellite cluster, for SUAV, mean and can carry more airborne equipment or farther voyage; For miniature missile, mean that can promote useful load accounts for full cartridge weight ratio, or increase scope.Development Minitype turbofan engine solves effective new departure of this difficult problem just.Turbofan engine, compared to turbojet engine, has lower oil consumption rate, better Economy.
Large-scale turbofan engine has thousands of big and small component, if directly that it is microminiaturized, then not only structure is too complicated for Minitype turbofan engine, and the part after microminiaturization is also difficult to processing.Therefore need to seek new approaches in the structural design of Minitype turbofan engine, to make the number of parts of tiny engine to the greatest extent can less, structure simplifies as far as possible, be easy to processing.Require that the part of design takes into account excellent aeroperformance and easy structural type on the one hand, require that attachment face (or mounting edge) number relating to assembling is the least possible on the other hand.
Because one of drawback that microminiaturization brings is that some part (as fan, the axle etc.) size of Minitype turbofan engine is comparatively large relative to the dimension scale of whole motor, and assembling surface of contact size between adjacent zeros parts is also larger relative to its characteristic size ratio.This makes the pneumatic profile of the initial designs of some structure influence on mating face, some step surface caused as installed, the bolt, nut, packing ring etc. of attachment face projection.These factors have impact on the performance of Minitype turbofan engine, and its adverse effect brought is much more serious than impact corresponding on large-scale turbofan engine.Therefore, artificer must take measures to avoid such aerodynamic loss as far as possible.
Adopt the inside and outside Minitype turbofan engine containing separately exhaust scheme, nozzle ring needs to assemble with Middle casing back segment, intension jet pipe, three due to intrinsic radial dimension poor, attachment face is made to be radial annular table terrace, be positioned at outer culvert outlet port, the air-flow of outer culvert ejection can produce whirlpool through this larger-size backward step, brings serious viscosity loss, the kinetic energy of outer culvert air-flow is reduced, causes the thrust loss of Minitype turbofan engine further.
Summary of the invention
Technical problem to be solved by this invention is for defect involved in background technique, a kind of Minitype turbofan engine with rectifier is provided to separate venting gas appliance, to reduce the exhaust loss of Minitype turbofan engine, make it obtain more high thrust and lower oil consumption rate, thus increase the Economy using this engine product.
The present invention is for solving the problems of the technologies described above by the following technical solutions:
Minitype turbofan engine with rectifier separates venting gas appliance, is positioned at the exhaust outlet position of turbofan engine, comprises outer culvert casing, Middle casing, nozzle box, rectifier, intension jet pipe and center cone;
Described outer culvert casing, Middle casing, nozzle box, intension jet pipe, rectifier, center cone connect successively, and wherein, the afterbody of described nozzle box is provided with the first flange mounting edge; The afterbody of Middle casing is provided with the second flange mounting edge; The front end of intension jet pipe is provided with three-flange mounting edge; Described rectifier is the conical surface shape of both ends open, and comparatively big uncork place is provided with the 4th flange mounting edge; On described first to fourth flange mounting edge, equal correspondence is provided with some mounting holes for interfixing, and first to fourth flange mounting edge arranges from the inside to the outside, interfixed by nut and bolt at each mounting hole place;
The difference of the described outer converging angles of culvert casing and the converging angles of Middle casing is within the scope of positive and negative 5 °;
The difference of the cone angle of described rectifier and the converging angles of intension jet pipe is within the scope of positive and negative 5 °;
The difference of the cone angle of described rectifier and the converging angles of Middle casing is within the scope of positive and negative 5 °.
Separate the further optimized project of venting gas appliance as the present invention with the Minitype turbofan engine of rectifier, the conical surface of described rectifier corresponds to each mounting hole and be provided with through hole.
Separate the further optimized project of venting gas appliance as the present invention with the Minitype turbofan engine of rectifier, the size of described through hole is 1.2 times of the diameter of bolt to 2 times.
Separate the further optimized project of venting gas appliance as the present invention with the Minitype turbofan engine of rectifier, the direction of the through hole on the described rectifier conical surface is vertical with the conical surface.
Separate the further optimized project of venting gas appliance as the present invention with the Minitype turbofan engine of rectifier, the exit position of described outer culvert casing and the initial position of Middle casing contraction section are at same axial position.
The present invention adopts above technological scheme compared with prior art, has following technique effect:
1. exhaust loss is little, structure is simple, quality is light;
2. add rectifier, the whirlpool loss that airflow passes backward step can be avoided to cause; In addition, the difference of intension jet pipe, tiny engine Middle casing, rectifier and outer culvert casing converging angles changes in the scope of positive and negative 5 °, makes air-flow can be more level and smooth to downstream transition, thus decreases the frictional loss of air-flow;
3. on the conical surface of rectifier, offered through hole, in the cavity that air-flow can be formed at rectifier and intension jet pipe, produced eddy current, strengthened the heat exchange of intension nozzle surface by the airflow circulating of inside, be conducive to the cooling of wall;
4. adopt distributed Placement Middle casing, nozzle box, intension jet pipe and rectifier to be connected, avoid bolt and connect four devices and be difficult to fastening problem, simple and reliable for structure.
Accompanying drawing explanation
Fig. 1 is that the Minitype turbofan engine of band rectifier separates venting gas appliance schematic diagram;
Fig. 2 is rectifier unit schematic diagram;
Fig. 3 is distributed Placement schematic diagram
In figure, 1-contains casing outward, 2-Middle casing, 3-nozzle box, 4-rectifier, 5-intension jet pipe, 6-center cone.
Embodiment
Below in conjunction with accompanying drawing, technological scheme of the present invention is described in further detail:
As shown in figures 1 and 3, the invention discloses a kind of Minitype turbofan engine with rectifier and separate venting gas appliance, be positioned at the exhaust outlet position of turbofan engine, comprise outer culvert casing, Middle casing, nozzle box, rectifier, intension jet pipe and center cone;
Described outer culvert casing, Middle casing, nozzle box, intension jet pipe, rectifier, center cone connect successively, and wherein, the afterbody of described nozzle box is provided with the first flange mounting edge; The afterbody of Middle casing is provided with the second flange mounting edge; The front end of intension jet pipe is provided with three-flange mounting edge;
As shown in Figure 2, described rectifier is the conical surface shape of both ends open, and comparatively big uncork place is provided with the 4th flange mounting edge; On described first to fourth flange mounting edge, equal correspondence is provided with some mounting holes for interfixing, and first to fourth flange mounting edge arranges from the inside to the outside, interfixed by nut and bolt at each mounting hole place;
The difference of the described outer converging angles of culvert casing and the converging angles of Middle casing is within the scope of positive and negative 5 °;
The difference of the cone angle of described rectifier and the converging angles of intension jet pipe is within the scope of positive and negative 5 °;
The difference of the cone angle of described rectifier and the converging angles of Middle casing is within the scope of positive and negative 5 °.
The conical surface of described rectifier corresponds to each mounting hole and be provided with through hole, the size of this through hole is 1.2 times of the diameter of bolt to 2 times, and direction is vertical with the conical surface.
The exit position of described outer culvert casing and the initial position of Middle casing contraction section are at same axial position.
In the process that intension jet pipe is connected with Middle casing, nozzle box, in most cases can produce backward step at the axial back segment of Middle casing, and be difficult to avoid, thus cause larger air-flow viscosity loss.As shown in Figure 1, in the axial rearward end of Middle casing, increase rectifier, and the converging angles α of the converging angles and the outer converging angles γ of culvert casing, the converging angles of rectifier and intension jet pipe that adjust rectifier changes within the scope of positive and negative 5 °, the viscosity loss that airflow passes backward step causes can be avoided thus, and air-flow smoothly can swim across transition downwards with less loss, thus reduce frictional loss and the mixing loss with main flow.The outer converging angles of culvert casing and the converging angles of Middle casing change within the scope of positive and negative 5 °.These four devices of Middle casing, nozzle box, intension jet pipe and rectifier are connected successively by flange mounting edge.
The axial rearward end of described outer culvert casing has a converging angles, and the converging angles γ of the size θ of converging angles and Middle casing changes within the scope of positive and negative 5 °.If consider the convenience of processing, outer culvert casing can be split into contraction section and flat segments, after separate machined completes, more in aggregates by being welded to connect.
On the flange mounting edge of described Middle casing, uniform the through hole of some of circumference, fixes for bolt.The initial position of its contraction section and the outlet of outer culvert casing are at same axial position A-A place.The centering of Middle casing can realize by being overlapped on nozzle box by mounting edge.
What described nozzle box adopted is high-temperature alloy material, if adopt casting processing, can be cast into a single piece with the stator of turbine.Axially afterbody has a flange mounting edge, for being connected with the flange mounting edge of Middle casing, rectifier, intension jet pipe, uniform through hole the same number of with Middle casing on flange mounting edge, the nut of identical number can be welded around through hole, such benefit is the feature can avoiding being difficult to tapping on refractory alloy, and convenient and easy.Nozzle box can retain the flat segments of certain distance in the axial rearward end of flange mounting edge, for the centering of Middle casing, rectifier, intension jet pipe.
The cone angle of described rectifier and the converging angles α of intension jet pipe change within the scope of positive and negative 5 °, namely | β-α |≤5 °.In order to construction bolt, the conical surface of rectifier is processed with the through hole consistent with number of through-holes on mounting edge.Take into account aeroperformance, avoid larger flow losses, on the conical surface, the size of through hole is chosen within 1.2 ~ 2 times of scopes of the diameter of bolt.On the conical surface, the size of through hole and position must ensure bolt energy normal mounting.Through hole offered by the conical surface of rectifier, has produced eddy current in the cavity that air-flow can be formed at rectifier and intension jet pipe, by the airflow circulating of inside, thus strengthen the heat exchange of intension jet pipe outer surface, be conducive to cooling.On the conical surface, the direction of through hole is set to vertical with the conical surface, and this mode is conducive to processing.
The correlation technique of the existing large Bypass Ratio Turbofan Engine of design considerations of the converging angles α on the described intension jet pipe conical surface and center cone has been come.Connection between center cone and intension jet pipe can adopt bolt to connect, in order to prevent gas leakage, can add a sleeve outside the bolt for connecting intension jet pipe and center cone, but its diameter can not be excessive in order to avoid affect air flow path, internal diameter can be taken as 1.2 ~ 1.4 times of the diameter of bolt.
Those skilled in the art of the present technique are understandable that, unless otherwise defined, all terms used herein (comprising technical term and scientific terminology) have the meaning identical with the general understanding of the those of ordinary skill in field belonging to the present invention.Should also be understood that those terms defined in such as general dictionary should be understood to have the meaning consistent with the meaning in the context of prior art, unless and define as here, can not explain by idealized or too formal implication.
Above-described embodiment; object of the present invention, technological scheme and beneficial effect are further described; be understood that; the foregoing is only the specific embodiment of the present invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. the Minitype turbofan engine with rectifier separates venting gas appliance, is positioned at the exhaust outlet position of turbofan turbofan engine, it is characterized in that, comprises outer culvert casing, Middle casing, nozzle box, rectifier, intension jet pipe and center cone;
Described outer culvert casing, Middle casing, nozzle box, intension jet pipe, rectifier, center cone connect successively, and wherein, the afterbody of described nozzle box is provided with the first flange mounting edge; The afterbody of Middle casing is provided with the second flange mounting edge; The front end of intension jet pipe is provided with three-flange mounting edge; Described rectifier is the conical surface shape of both ends open, and comparatively big uncork place is provided with the 4th flange mounting edge; On described first to fourth flange mounting edge, equal correspondence is provided with some mounting holes for interfixing, and first to fourth flange mounting edge arranges from the inside to the outside, interfixed by nut and bolt at each mounting hole place;
The difference of the described outer converging angles of culvert casing and the converging angles of Middle casing is within the scope of positive and negative 5 °;
The difference of the cone angle of described rectifier and the converging angles of intension jet pipe is within the scope of positive and negative 5 °;
The difference of the cone angle of described rectifier and the converging angles of Middle casing is within the scope of positive and negative 5 °.
2. the Minitype turbofan engine with rectifier according to claim 1 separates venting gas appliance, it is characterized in that, the conical surface of described rectifier corresponds to each mounting hole and is provided with through hole.
3. the Minitype turbofan engine with rectifier according to claim 2 separates venting gas appliance, it is characterized in that, the size of described through hole is 1.2 times of the diameter of bolt to 2 times.
4. the Minitype turbofan engine with rectifier according to claim 2 separates venting gas appliance, it is characterized in that, the direction of the through hole on the described rectifier conical surface is vertical with the conical surface.
5. the Minitype turbofan engine with rectifier according to claim 1 separates venting gas appliance, it is characterized in that, the exit position of described outer culvert casing and the initial position of Middle casing contraction section are at same axial position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510899841.5A CN105422313B (en) | 2015-12-09 | 2015-12-09 | Miniature turbofan engine separate exhausting device with rectifier |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510899841.5A CN105422313B (en) | 2015-12-09 | 2015-12-09 | Miniature turbofan engine separate exhausting device with rectifier |
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| CN105422313A true CN105422313A (en) | 2016-03-23 |
| CN105422313B CN105422313B (en) | 2017-04-19 |
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| CN201510899841.5A Expired - Fee Related CN105422313B (en) | 2015-12-09 | 2015-12-09 | Miniature turbofan engine separate exhausting device with rectifier |
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Cited By (3)
| 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 |
| CN113944565A (en) * | 2021-10-19 | 2022-01-18 | 中国科学院工程热物理研究所 | Tail nozzle structure for improving vibration characteristic |
| CN114856857A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Integrated type round-square casing with multiple channels |
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| CN205277627U (en) * | 2015-12-09 | 2016-06-01 | 南京航空航天大学 | Miniature turbofan engine divides division exhaust apparatus with rectifier |
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2015
- 2015-12-09 CN CN201510899841.5A patent/CN105422313B/en not_active Expired - Fee Related
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| US7437877B2 (en) * | 2004-02-13 | 2008-10-21 | Honda Motor Co., Ltd. | Compressor having low-pressure and high-pressure compressor operating at optimum ratio between pressure ratios thereof and gas turbine engine adopting the same |
| US7762057B2 (en) * | 2007-06-05 | 2010-07-27 | The Boeing Company | Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines |
| CN103703237A (en) * | 2011-07-25 | 2014-04-02 | 埃尔塞乐公司 | Device for connecting front frame to fan casing |
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Cited By (6)
| 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 |
| CN113944565A (en) * | 2021-10-19 | 2022-01-18 | 中国科学院工程热物理研究所 | Tail nozzle structure for improving vibration characteristic |
| CN113944565B (en) * | 2021-10-19 | 2022-06-28 | 中国科学院工程热物理研究所 | Tail nozzle structure for improving vibration characteristic |
| CN114856857A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Integrated type round-square casing with multiple channels |
| CN114856857B (en) * | 2022-05-12 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Multi-channel integrated round-square casing |
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| CN105422313B (en) | 2017-04-19 |
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Granted publication date: 20170419 Termination date: 20201209 |