CN205277599U - Flow splitter and aeroengine - Google Patents
Flow splitter and aeroengine Download PDFInfo
- Publication number
- CN205277599U CN205277599U CN201620029877.8U CN201620029877U CN205277599U CN 205277599 U CN205277599 U CN 205277599U CN 201620029877 U CN201620029877 U CN 201620029877U CN 205277599 U CN205277599 U CN 205277599U
- Authority
- CN
- China
- Prior art keywords
- mouth
- flow splitter
- combustion chamber
- utility
- rear end
- 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.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 34
- 230000007704 transition Effects 0.000 claims description 8
- 230000008901 benefit Effects 0.000 abstract description 7
- 238000010923 batch production Methods 0.000 abstract description 3
- 230000008878 coupling Effects 0.000 abstract 2
- 238000010168 coupling process Methods 0.000 abstract 2
- 238000005859 coupling reaction Methods 0.000 abstract 2
- 238000010586 diagram Methods 0.000 description 8
- 238000012217 deletion Methods 0.000 description 4
- 230000037430 deletion Effects 0.000 description 4
- 238000007634 remodeling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a flow splitter and aeroengine, flow splitter include body, front end tang and rear end tang, the body is the annular structure, the front end tang is this body coupling in the port of compressor one end, and front end tang inner wall is equipped with a plurality of blade stators, the rear end tang is this body coupling in the port of combustion chamber one end, and the rear end tang feeds through in the front end tang, and the internal diameter of front end tang is lighter than the internal diameter of rear end tang. The utility model provides a flow splitter, through connecting the structural design who sets up the blade stator in the front end tang inner wall of compressor one end at it, make the flow splitter to draw air flow field more even. The utility model provides an aeroengine is owing to be provided with above -mentioned flow splitter for arouse that the flow field weakens the influence of mainstream field, improved aeroengine's performance. In addition, this flow splitter simple structure, reliable is suitable for batch production, has higher economic benefits.
Description
Technical field
The utility model relates to aero engine technology field, specifically, it relates to a kind of flow splitter and have the aircraft engine of this flow splitter.
Background technology
In the auxiliary powerplant of existing aircraft engine is studied, due to auxiliary powerplant operationally, pneumatic plant should provide stable uniform air flow for combustion chamber, needs again for sustainer provides high-pressure bleed air gas source. Therefore, pneumatic plant is for, after sustainer offer bleed, whether the air-flow entering combustion chamber is uniform and stable, directly affects the margin of operation of auxiliary powerplant. Therefore, in order to enable auxiliary powerplant meet the manufacture claim of relatively high workload nargin, the design of flow splitter then becomes the most important thing of auxiliary powerplant research.
The flow splitter that existing auxiliary powerplant adopts usually when bleed is shunted is as shown in Figure 1, this kind of flow splitter mainly comprises body 10, front end only mouth 20 and rear end only mouth 30, owing to the ramp structure of mouth 20 is stopped in its front end, make local bleed mass flow discrepancy, the angle of attack of the axial diffuser-in this region is caused to increase, and then affect the surge nargin of centrifugal pneumatic plant, blower outlet flow field also can be caused uneven. Cause the air-flow being supplied to combustion chamber uneven so that the situation of Partial ablation usually occurs turbine guider, or causes combustion chamber, because local flow crosses little, carbon deposition phenomenon occurs. Further, above-mentioned flow splitter is relatively big owing to joining mixed loss when bleed, causes bleed air pressure loss also bigger.
Practical novel content
A main purpose of the present utility model is to overcome at least one defect of above-mentioned prior art, it is provided that a kind of bleed flow and the uniform flow splitter of gas supply flow.
Another main purpose of the present utility model is to overcome at least one defect of above-mentioned prior art, it is provided that a kind of excellent property and aircraft engine simple and reliable for structure.
For achieving the above object, the utility model adopts following technical scheme:
According to an aspect of the present utility model, it is provided that a kind of flow splitter, for being connected between pneumatic plant and combustion chamber, wherein, described flow splitter comprises body, front end only mouth and rear end only mouth; Described body structure in the form of a ring; Described front end only mouth be the port that described body is connected to described pneumatic plant one end, and described front end only mouth inwall be provided with multiple blade stator; Described rear end only mouth be the port that described body is connected to one end, described combustion chamber, described rear end only mouth be communicated in described front end only mouth, and the internal diameter of described front end only mouth is less than the internal diameter of described rear end only mouth.
According to one of them enforcement mode of the present utility model, between the setting direction of described blade stator and the axial direction due of described body, there is an angle.
According to one of them enforcement mode of the present utility model, described angle is 20 �㡫80 ��.
According to one of them enforcement mode of the present utility model, each described blade stator is arranged in parallel; And/or, described multiple blade stator stops interval on the periphery of mouth inwall and is uniformly distributed in described front end.
According to of the present utility model one of them implement mode, described blade stator equals the degree of depth of described front end only mouth in described body shaft projecting length upwards.
According to of the present utility model one of them implement mode, described blade stator has and is connected to the only root of mouth inwall and the end that extends by described root, described front end, and the thickness of the root of described blade stator is greater than the thickness of end.
According to of the present utility model one of them implement mode, the inwall with the only junction of mouth, described front end of described rear end only mouth has transition structure.
According to one of them enforcement mode of the present utility model, described transition structure is arc or wedge shape face.
According to one of them enforcement mode of the present utility model, the position that mouth and Zhi Kou junction, described rear end are stopped corresponding to described front end in described body periphery is provided with joint flange, to connect described pneumatic plant and combustion chamber respectively.
According to another aspect of the present utility model, a kind of aircraft engine is provided, comprise pneumatic plant and combustion chamber, wherein, described aircraft engine also comprises described flow splitter, described flow splitter is connected between described pneumatic plant and combustion chamber, and the centrifugal casing that mouth is communicated in described pneumatic plant is stopped in the front end of described flow splitter, and the combustion chamber casing that mouth is communicated in described combustion chamber is stopped in described rear end.
As shown from the above technical solution, the flow splitter that the utility model proposes and the advantage of aircraft engine and positively effect are:
The flow splitter that the utility model proposes, stops, by the front end being connected to pneumatic plant one end at it, the structure design that mouth inwall arranges blade stator, makes the bleed flow field of flow splitter more even. The aircraft engine that the utility model proposes, owing to being provided with above-mentioned flow splitter so that cause flow field the impact of main flow field to be weakened, it is to increase the performance of aircraft engine. In addition, this flow splitter structure is simple, reliable, is suitable for batch production, has higher economic benefit.
Accompanying drawing explanation
Considering the following detailed explanation to preferred implementation of the present utility model in conjunction with the drawings, various target of the present utility model, feature and advantage will become more apparent. Accompanying drawing is only exemplary diagram of the present utility model, and not necessarily is drawn in proportion. In the accompanying drawings, same Reference numeral represents same or similar parts all the time. Wherein:
Fig. 1 is the partial cutaway TV structure schematic diagram of a kind of existing flow splitter;
Fig. 2 is the sectional structure schematic diagram of a kind of flow splitter according to an illustrative embodiments;
Fig. 3 is the partial cutaway TV structure schematic diagram done along B-B straight line in Fig. 2;
Fig. 4 is the partial cutaway TV structure schematic diagram done along C-C straight line in Fig. 2.
Wherein, description of reference numerals is as follows:
10. body; 20. front ends are mouth only; 30. rear ends are mouth only; 1. body; 11. joint flanges; 2. front end only mouth; 21. blade stators; 3. rear end only mouth; 31. transition structures; A. axially; ��. angle.
Embodiment
The exemplary embodiments embodying the utility model feature & benefits will describe in the following description in detail. Iting should be understood that the utility model can have various changes in different embodiments, it does not all depart from scope of the present utility model, and explanation and accompanying drawing wherein is being the use explained in essence, and is not used to restriction the utility model.
To in the following describes of different illustrative embodiments of the present utility model, carry out with reference to accompanying drawing, described accompanying drawing forms a part of the present utility model, and wherein shows different example arrangement, system and the step that can realize many aspects of the present utility model by way of example. It will be understood that other specified scheme of parts, structure, exemplary means, system and step can be used, and structure and function amendment can be carried out when not deviateing the utility model scope. And, although this specification sheets can use term " end ", " periphery ", " between ", " interior " etc. different example feature of the present utility model and element are described, but these terms are used for herein only for convenience, such as with reference to the accompanying drawings described in the direction of example. The specific three dimensional direction that any content in this specification sheets all should not be construed as Structure of need just falls in scope of the present utility model.
Flow splitter implements mode
Consult Fig. 2, Fig. 2 representatively illustrates the sectional structure schematic diagram of the flow splitter that can embody principle of the present utility model. In this illustrative embodiments, the flow splitter that the utility model proposes is for aircraft engine, further, it is the flow splitter to be connected between the pneumatic plant of aircraft engine and combustion chamber, the docking structure of flow splitter and pneumatic plant and combustion chamber is described. Those skilled in the art it is easily understood that, for this flow splitter is applied in the aircraft engine of other kinds, and following embodiment is made multiple remodeling, interpolation, replacement, deletion or other changes, these changes are still in the scope of the principle of the flow splitter that the utility model proposes.
As shown in Figure 2, in the present embodiment, the flow splitter that the utility model proposes is for being connected between pneumatic plant and combustion chamber, and this flow splitter mainly comprises body 1, front end, and only mouth 3 is stopped in mouth 2 and rear end.
As shown in Figure 2, in the present embodiment, this body 1 structure in the form of a ring. Specifically, this body 1 is in circular ring, and the aircraft engine for different structure form, the ring texture shape of this body 1 can according to aircraft engine, particularly the concrete structure of pneumatic plant and combustion chamber and adjust flexibly, not as limit.
As shown in Figure 2, in the present embodiment, front end only mouth 2 be the port that body 1 is connected to pneumatic plant one end, and front end is stopped mouth 2 inwall and is provided with multiple blade stator 21. These blade stators 21 are arranged in parallel, and multiple blade stator 21 interval on the periphery of front end only mouth 2 inwall is uniformly distributed. Further, the projecting length of blade stator 21 on the axial A of body 1 equals the degree of depth of front end only mouth 2. Simultaneously please refer to the partial cutaway TV structure schematic diagram of a kind of flow splitter representatively illustrating present embodiment in Fig. 3 and Fig. 4, Fig. 3, it specifically represents the cross sectional view of blade tip. Representatively illustrating the partial cutaway TV structure schematic diagram of a kind of flow splitter of present embodiment in Fig. 4, it specifically represents the interface view of root of blade. As shown in Figure 3 and Figure 4, in the present embodiment, between the setting direction of blade stator 21 and the axial A direction of body 1, there is an angle ��, and the concrete value that this angle �� can be preferably 20 �㡫80 �� of these angle �� can adjust flexibly according to the different demands of different types of aircraft engine, choose any angle of 0 �㡫90 �� (namely 0 �㡫180 ��). In addition, blade stator 21 has and is connected to the only root of mouth 2 inwall and the end that extends by root, front end, and the thickness of the root of blade stator 21 is greater than the thickness of end, that is, each blade stator 21 is to the thinning gradually structure of its end thickness by its root. Those skilled in the art it is easily understood that, for above-mentioned blade stator 21 being arranged at front end only mouth 2 inwall, and the structure and set-up mode to the quantity of above-mentioned blade stator 21, distribution mode, each blade stator 21 makes multiple remodeling, interpolation, replacement, deletion or other changes, these changes are still in the scope of the principle of the flow splitter that the utility model proposes.
As shown in Figure 2, in the present embodiment, rear end only mouth 3 be the port that body 1 is connected to one end, combustion chamber, rear end only mouth 3 be communicated in front end only mouth 2, and the internal diameter of front end only mouth 2 is less than the internal diameter that mouth 3 is stopped in rear end. Wherein, the inwall with the only junction of mouth 2, front end of rear end only mouth 3 has transition structure 31. In the present embodiment, this transition structure 31 can be preferably arc. Those skilled in the art it is easily understood that, for arranging above-mentioned rear end only mouth 3, and above-mentioned rear end is stopped the structure of mouth 3, particularly the shape of transition structure 31 or decoration form make multiple remodeling, interpolation, replacement, deletion or other changes, and these changes are still in the scope of the principle of the flow splitter that the utility model proposes.
At this it is noted that shown in accompanying drawing and the flow splitter described in this manual be only to adopt an example in many kinds of flow splitters of the utility model principle. It should be clearly understood that principle of the present utility model is only limitted to absolutely not shown in accompanying drawing or any details of flow splitter of describing in this specification sheets or any parts of flow splitter.
For example, it is not intended to meet principle of the present utility model, as shown in Figure 2, in the present embodiment, body 1 periphery is provided with joint flange 11 corresponding to the position of only mouth 2 and rear end only mouth 3 junction, front end, by respectively by screw with multiple fixed orifices offered by joint flange 11 in the way of be connected pneumatic plant and combustion chamber.
But, not in each enforcement mode of the present utility model, it is necessary to above-mentioned joint flange 11 is set, namely by above-mentioned mode of connection, the flow splitter that the utility model proposes is connected between the pneumatic plant of aircraft engine and combustion chamber. Those skilled in the art it is easily understood that, for this flow splitter is connected between pneumatic plant and combustion chamber, and the structure of above-mentioned joint flange 11 or flow splitter body 1 is made multiple remodeling, interpolation, replacement, deletion or other changes, these changes are still in the scope of the principle of the flow splitter that the utility model proposes.
Aircraft engine implements mode
Below in conjunction with an illustrative embodiments, structure and principle to the aircraft engine that the utility model proposes are further described.
In the present embodiment, the aircraft engine that the utility model proposes mainly comprises pneumatic plant and combustion chamber, and pneumatic plant can be centrifugal pneumatic plant, and has centrifugal casing, and combustion chamber has combustion chamber casing. Wherein, this aircraft engine also comprises the flow splitter that the utility model proposes, and this flow splitter is connected between pneumatic plant and combustion chamber. Specifically, the centrifugal casing that mouth 2 is communicated in pneumatic plant is stopped in the front end of this flow splitter, and the combustion chamber casing that mouth 3 is communicated in combustion chamber is stopped in rear end.
From the above, based on the structure of above-mentioned aircraft engine particularly flow splitter, the roughly principle of work of the flow splitter that the utility model proposes when being applied to aircraft engine is as follows:
Via the high pressure draft after the centrifugal impeller of centrifugal pneumatic plant and radial diffuser supercharging, a part enters combustion chamber by the axial A of the body 1 of flow splitter, and another part is entered among the spiral case of centrifugal casing by the shunting of flow splitter. Before a point air-flow enters spiral case, the blade stator 21 of this part air-flow on flow splitter has carried out rectification, can reach the bleed shunting effect of flow splitter the best.
As shown from the above technical solution, the flow splitter that the utility model proposes and the advantage of aircraft engine and positively effect are:
The flow splitter that the utility model proposes, stops, by the front end being connected to pneumatic plant one end at it, the structure design that mouth inwall arranges blade stator, makes the bleed flow field of flow splitter more even. The aircraft engine that the utility model proposes, owing to being provided with above-mentioned flow splitter so that cause flow field the impact of main flow field to be weakened, it is to increase the performance of aircraft engine. In addition, this flow splitter structure is simple, reliable, is suitable for batch production, has higher economic benefit.
Below describe in detail and/or illustrate the illustrative embodiments of flow splitter and the aircraft engine that the utility model proposes. But enforcement mode of the present utility model is not limited to particular implementation as described herein, on the contrary, each implements the integral part of mode and/or step can be used separately with other integral part as described herein and/or step independent sum. Implement each integral part of mode and/or each step also can implement other integral part of mode with other and/or step is combined for one. When introducing described and/or illustrated key element/integral part/wait here, term " ", " one " and " above-mentioned " etc. in order to expression exist one or more key element/integral part/etc. Term " comprises ", " comprising " and " having " in order to also can exist except representing the open meaning that included and referring to the key element/integral part except listing/wait other key element/integral part/etc. In addition, term " first " in claim book and specification sheets and " the 2nd " etc. only use as mark, are not the numerical limit to its object.
Although the flow splitter that the utility model proposes and aircraft engine being described according to different specific embodiments, but those skilled in the art will recognize that and enforcement of the present utility model can be changed in the spirit and scope of claim.
Claims (10)
1. a flow splitter, for being connected between pneumatic plant and combustion chamber, it is characterised in that, described flow splitter comprises:
Body (1), structure in the form of a ring;
Front end only mouth (2), for described body (1) is connected to the port of described pneumatic plant one end, and described front end only mouth (2) inwall be provided with multiple blade stator (21); And
Rear end is mouth (3) only, for described body (1) is connected to the port of one end, described combustion chamber, described rear end only mouth (3) be communicated in described front end only mouth (2), and the internal diameter of described front end only mouth (2) is less than the internal diameter of described rear end only mouth (3).
2. flow splitter according to claim 1, it is characterised in that, between the setting direction of described blade stator (21) and axis (A) direction of described body (1), there is an angle (��).
3. flow splitter according to claim 2, it is characterised in that, described angle (��) is 20 �㡫80 ��.
4. flow splitter according to claim 2, it is characterised in that, each described blade stator (21) is arranged in parallel; And/or
Described multiple blade stator (21) is stopped interval on the periphery of mouth (2) inwall and is uniformly distributed in described front end.
5. flow splitter according to claim 1, it is characterised in that, the projecting length of described blade stator (21) on described body (1) axially (A) equals the degree of depth that mouth (2) is stopped in described front end.
6. flow splitter according to the arbitrary item of Claims 1 to 5, it is characterized in that, described blade stator (21) has and is connected to the only root of mouth (2) inwall and the end that extends by described root, described front end, and the thickness of the root of described blade stator (21) is greater than the thickness of end.
7. flow splitter according to claim 6, it is characterised in that, the inwall with the only junction of mouth (2), described front end of described rear end only mouth (3) has transition structure (31).
8. flow splitter according to claim 7, it is characterised in that, described transition structure (31) is arc or wedge shape face.
9. flow splitter according to claim 1, it is characterized in that, described body (1) periphery is provided with joint flange (11) corresponding to the position that only mouth (3) junction is stopped in mouth (2) and described rear end, described front end, to connect described pneumatic plant and combustion chamber respectively.
10. an aircraft engine, comprise pneumatic plant and combustion chamber, it is characterized in that, described aircraft engine also comprises the flow splitter as described in item as arbitrary in claim 1��9, described flow splitter is connected between described pneumatic plant and combustion chamber, the centrifugal casing that mouth (2) is communicated in described pneumatic plant is stopped in the front end of described flow splitter, and the combustion chamber casing that mouth (3) is communicated in described combustion chamber is stopped in described rear end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620029877.8U CN205277599U (en) | 2016-01-13 | 2016-01-13 | Flow splitter and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620029877.8U CN205277599U (en) | 2016-01-13 | 2016-01-13 | Flow splitter and aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205277599U true CN205277599U (en) | 2016-06-01 |
Family
ID=56062180
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620029877.8U Active CN205277599U (en) | 2016-01-13 | 2016-01-13 | Flow splitter and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205277599U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107524522A (en) * | 2016-06-20 | 2017-12-29 | 中国航发商用航空发动机有限责任公司 | Receive expansion formula fanjet flow splitter |
-
2016
- 2016-01-13 CN CN201620029877.8U patent/CN205277599U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107524522A (en) * | 2016-06-20 | 2017-12-29 | 中国航发商用航空发动机有限责任公司 | Receive expansion formula fanjet flow splitter |
| CN107524522B (en) * | 2016-06-20 | 2021-06-11 | 中国航发商用航空发动机有限责任公司 | Collecting and expanding type turbofan engine flow distribution ring |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101021181B (en) | Double bypass turbofan | |
| CN104675556B (en) | The large Bypass Ratio Turbofan Engine of blade tip reaction driving fan | |
| CA2520471C (en) | Methods and apparatus for assembling a gas turbine engine | |
| US20190186381A1 (en) | Intergrated environmental control system manifold | |
| CN106642199A (en) | Thermally coupled CMC combustor liner | |
| CN105371300A (en) | Downstream nozzle for combustor of combustion turbine engine and delay injector | |
| CN104279010A (en) | Splitter with a sheet forming a guide surface for the flow and a defrosting channel | |
| CN206352838U (en) | A kind of annular burner | |
| CN106593694B (en) | A kind of centripetal turbine fan jet engine | |
| US10415466B2 (en) | Offset cores for gas turbine engines | |
| CN103062795B (en) | Transition nozzle | |
| US10054059B2 (en) | Nacelle and compressor inlet arrangements | |
| CN104879320A (en) | Surging-prevent compressor volute structure for turbocharger | |
| CN205277599U (en) | Flow splitter and aeroengine | |
| CN203614229U (en) | Fusion outer bypass outlet guide vane support plate structure of engine and aero-engine | |
| CN103438026B (en) | The centrifugal compressor of intergrade bleed | |
| US20150330254A1 (en) | Compact Nacelle With Contoured Fan Nozzle | |
| US10167088B2 (en) | Crosswind performance aircraft engine spinner | |
| CN102356279A (en) | Method for operating burner and burner, in particular for gas turbine | |
| CN102235267B (en) | Gas turbine engine modified by using retired turbofan engine through low-pressure crest truncation | |
| CN102829002B (en) | Small-size annular nozzle ejector with exchangeable throat part | |
| US9885285B2 (en) | Gas turbine engine nacelle | |
| EP3536902B1 (en) | Gas turbine engine component | |
| CN106907741A (en) | A kind of chamber structure | |
| JP4143901B2 (en) | Turbofan engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |