CN109060293B - Method for improving air inflow of injection type nacelle - Google Patents
Method for improving air inflow of injection type nacelle Download PDFInfo
- Publication number
- CN109060293B CN109060293B CN201811053680.8A CN201811053680A CN109060293B CN 109060293 B CN109060293 B CN 109060293B CN 201811053680 A CN201811053680 A CN 201811053680A CN 109060293 B CN109060293 B CN 109060293B
- Authority
- CN
- China
- Prior art keywords
- nacelle
- flow
- injection type
- wall surface
- flow guide
- 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
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a method for improving the air intake flow of an injection type nacelle, wherein the injection type nacelle comprises a nacelle inlet, a nacelle wall surface and a nacelle outlet, a plurality of groups of sonic nozzles are arranged in the injection type nacelle, and a flow guide structure from inside to outside is arranged on the nacelle wall; according to the invention, the guide grid is arranged at the upstream of the outlet of the jet nacelle, and the guide vane is arranged to guide part of mixed airflow of high-speed jet flow and low-speed jet flow to the tail part of the jet nacelle, so that the congestion effect caused by the convergent nozzle is reduced, and the air intake flow of the jet nacelle can be obviously improved.
Description
Technical Field
The invention relates to the field of experimental aerodynamics, in particular to a method for improving the air inflow of an injection type nacelle.
Background
In order to research the influence of the air intake and exhaust of the turbofan aircraft engine on the aerodynamic characteristics of the aircraft, a dynamic simulation test needs to be performed in a wind tunnel, and an injection type nacelle is one of simulation modes. The jet-propelled nacelle is a simulator of a turbofan engine in a wind tunnel and is used for simulating the influence of air intake and exhaust of the engine on the aerodynamic characteristics of an airplane. The jet-propelled nacelle is driven by high-pressure air, the high-pressure air is jetted into the nacelle through the sonic nozzle to generate high-speed jet flow, ambient air enters the nacelle from the inlet of the nacelle and flows under the jet action of the high-speed jet flow to form low-speed jet air flow, and the low-speed jet air flow and the high-speed jet air flow are fully mixed and then are discharged through the outlet of the nacelle, as shown in figure 1. The air inflow of the injection type nacelle is an important index of the simulation capability of the injection type nacelle. However, the jet-type nacelle usually adopts a convergent nozzle, when the drop pressure ratio of the jet-type nacelle outlet is higher (greater than 1.5), a congestion effect is generated at the nacelle outlet by high-speed jet flow and low-speed jet flow, so that the simulation capability of the nacelle air intake is reduced rapidly, and when the drop pressure ratio of the jet-type nacelle outlet is further increased, the nacelle inlet even generates backflow, which seriously affects the simulation effect of the jet-type nacelle air intake.
Disclosure of Invention
The invention aims to solve the problems, provides a method for improving the air inflow of an injection type nacelle, solves the congestion effect caused by a convergent nozzle and improves the air inflow.
In order to achieve the purpose, the invention adopts the following technical scheme:
the method for improving the air intake flow of the injection type nacelle comprises the steps that the injection type nacelle comprises a nacelle inlet, a nacelle wall surface and a nacelle outlet, a plurality of groups of sonic nozzles are arranged in the injection type nacelle, and a flow guide structure from inside to outside is arranged on the nacelle wall.
In the above technical solution, the diversion structure includes a diversion grating disposed on the nacelle wall and a diversion sheet disposed on the nacelle inner wall.
In the above technical scheme, the flow guide grid is arranged on the tail part of the wall surface of the nacelle at the nacelle outlet.
In the technical scheme, at least four groups of flow guide grids are arranged on the wall surface of the nacelle, and each group of flow guide grids can be independently disassembled and assembled.
In the technical scheme, the multiple groups of flow guide grids are uniformly distributed on the same circumference of the wall surface of the nacelle of the injection nacelle.
In the above technical solution, the guide grids of each group can be freely closed.
In the technical scheme, the guide grids of all the groups can be combined for use, so that different guide modes are realized.
In the technical scheme, the flow deflector is arranged on the inner wall surface of the nacelle and positioned at the upstream position of the nacelle outlet, and is used for shunting part of mixed airflow of high-speed jet flow and low-speed injected airflow to the flow guide grid.
In the technical scheme, the groups of sonic nozzles are uniformly distributed on the same circumferential surface.
In the technical scheme, the groups of sonic nozzles form circular ring arrays with different radiuses from the inside to the outside.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
according to the invention, the guide grid is arranged at the upstream of the outlet of the jet nacelle, and the guide vane is arranged to guide part of mixed airflow of high-speed jet flow and low-speed jet flow to the tail part of the jet nacelle, so that the congestion effect caused by the convergent nozzle is reduced, and the air intake flow of the jet nacelle can be obviously improved.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 and FIG. 2 are schematic structural views of an injection nacelle;
wherein: 1 is a nacelle inlet, 2 is a sonic nozzle, 3 is a nacelle outlet, 4 is a flow guide grid, and 5 is a flow guide vane.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
The jet-type nacelle is driven by high-pressure air, the high-pressure air is jetted into the nacelle through the sonic nozzle to generate high-speed jet flow, ambient air enters the nacelle from the inlet of the nacelle and flows under the jet action of the high-speed jet flow to form low-speed jet air flow, and the low-speed jet air flow and the high-speed jet air flow are fully mixed and then discharged from the outlet of the nacelle, wherein the figure is 1.
According to the method for improving the air inlet flow of the injection type nacelle, the guide vane is arranged at the upstream position of the inner wall surface of the nacelle positioned at the outlet of the nacelle, and part of mixed airflow of high-speed jet flow and low-speed injected airflow is distributed to the guide grid. And part of mixed airflow of the high-speed jet flow and the low-speed ejected airflow is guided out to the tail part of the nacelle through the flow guide grid. The flow of the air flow passing through the outlet of the nacelle is reduced by the part of the branched mixed air flow, and the congestion effect caused by the convergent nozzle is reduced, so that the air inlet flow of the jet nacelle is improved. The guide grid divides the mixed gas into a plurality of jet flows, and the plurality of jet flows can be mixed with the main jet flow passing through the nacelle outlet again by optimizing the grid position and grid parameters (angle, profile and the like), so that the influence of the bypass flow on the aerodynamic characteristics of the airplane is reduced to the minimum.
The water conservancy diversion grid can make up the use, and is nimble convenient, and expansibility is strong. A plurality of groups (more than or equal to 4 groups) of diversion gratings are arranged around the nacelle, and each group can be independently disassembled and assembled, as shown in figure 2. During the in-service use, can be according to the characteristics of aircraft model, have pertinence to close the water conservancy diversion grid of certain direction, it is nimble convenient, expansibility is strong. If a certain aircraft engine nacelle is arranged below a wing, because the nacelle is close to the wing, airflow discharged by a flow guide grid at the upper part of the nacelle can directly flow onto the wing to generate acting force on the wing, and extra errors can be brought to a power simulation test result.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (8)
1. The method for improving the air intake flow of the injection type nacelle comprises a nacelle inlet, a nacelle wall surface and a nacelle outlet and is characterized in that a plurality of groups of sonic nozzles are arranged in the injection type nacelle, a flow guide structure from inside to outside is arranged on the nacelle wall surface, and the flow guide structure comprises a flow guide grid arranged on the tail part of the nacelle wall surface of the nacelle outlet and a flow guide sheet arranged on the inner wall of the nacelle.
2. The method for improving the intake air flow of the injection type nacelle according to claim 1, wherein the wall surface of the nacelle is provided with at least four sets of flow guide grilles, and each set of flow guide grilles can be independently assembled and disassembled.
3. The method for increasing the intake air flow of the injection type nacelle according to claim 2, wherein the multiple sets of flow guide grids are uniformly distributed on the same circumference of the wall surface of the nacelle of the injection type nacelle.
4. The method of claim 2, wherein the flow directing grill of each set is freely closable.
5. The method of claim 3, wherein all sets of flow grids are used in combination to achieve different flow patterns.
6. The method for improving the intake air flow of the injection type nacelle according to claim 1, wherein the flow deflector is disposed on the inner wall surface of the nacelle at a position upstream of the outlet of the nacelle for diverting a part of the mixed air flow of the high-speed jet flow and the low-speed injected air flow to the flow guide grid.
7. The method for increasing the air intake flow of the injection type nacelle according to claim 1, wherein the plurality of sets of sonic nozzles are uniformly distributed on the same circumferential surface.
8. The method of claim 7, wherein the plurality of sonic nozzles are arranged in an array of rings of different radii from the inside to the outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811053680.8A CN109060293B (en) | 2018-09-11 | 2018-09-11 | Method for improving air inflow of injection type nacelle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811053680.8A CN109060293B (en) | 2018-09-11 | 2018-09-11 | Method for improving air inflow of injection type nacelle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109060293A CN109060293A (en) | 2018-12-21 |
| CN109060293B true CN109060293B (en) | 2020-07-28 |
Family
ID=64761084
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811053680.8A Active CN109060293B (en) | 2018-09-11 | 2018-09-11 | Method for improving air inflow of injection type nacelle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109060293B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650791B (en) * | 2021-09-08 | 2022-10-25 | 中国商用飞机有限责任公司 | Nacelle and aircraft equipped with same |
| CN113942630B (en) * | 2021-10-09 | 2023-04-28 | 中国直升机设计研究所 | Airfoil and aircraft capable of generating lift force and thrust force based on airflow injection effect |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2465481C2 (en) * | 2010-12-06 | 2012-10-27 | Владимир Тарасович Шведов | Vortex propeller |
| WO2014202881A1 (en) * | 2013-06-18 | 2014-12-24 | Snecma | Ventilation of a turbomachine nacelle |
| CN108019294A (en) * | 2016-11-04 | 2018-05-11 | 北京航空航天大学 | A kind of nozzles with injector with guide rib suppresses return-flow structure |
-
2018
- 2018-09-11 CN CN201811053680.8A patent/CN109060293B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2465481C2 (en) * | 2010-12-06 | 2012-10-27 | Владимир Тарасович Шведов | Vortex propeller |
| WO2014202881A1 (en) * | 2013-06-18 | 2014-12-24 | Snecma | Ventilation of a turbomachine nacelle |
| CN108019294A (en) * | 2016-11-04 | 2018-05-11 | 北京航空航天大学 | A kind of nozzles with injector with guide rib suppresses return-flow structure |
Non-Patent Citations (1)
| Title |
|---|
| 低速风洞引射短舱动力模拟技术新进展;章荣平 等;《空气动力学报》;20161231;第34卷(第6期);第756-761页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109060293A (en) | 2018-12-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102216604B (en) | Turbine with mixers and ejectors | |
| CN107687948B (en) | Air inlet total pressure and vortex flow coupling distortion generator and distortion test method | |
| US4175640A (en) | Vortex generators for internal mixing in a turbofan engine | |
| US4298089A (en) | Vortex generators for internal mixing in a turbofan engine | |
| CN105424309B (en) | A kind of mono-/bis-duct mode transition procedure air-flow dynamic rerponse test stand | |
| CN109060293B (en) | Method for improving air inflow of injection type nacelle | |
| CN106837550A (en) | The method for designing of hypersonic triple channel air intake duct | |
| CN109670269B (en) | Design method of multi-channel parallel three-power combined engine | |
| CN104847708B (en) | Supersonic Ejector | |
| CN110083869A (en) | A kind of calculation method that evaluation profile transformation influences whirlpool spray/turbofan variable cycle engine stability margin | |
| CN106546433A (en) | The direct-connected assay device of scramjet engine of alternative free jet test and method for designing | |
| CN109339875B (en) | A kind of mixing diffuser of band bypass bleed | |
| CN113418713B (en) | Combined distortion generator of engine | |
| CN108561244A (en) | A kind of three power combination engine design methods that super burn coexists with sub- combustion combustion chamber | |
| CN112229639B (en) | Design method of aero-engine intake total pressure distortion generation device | |
| RU2531432C2 (en) | Development of vtol aircraft drive forces and aircraft to this end | |
| CN103835810A (en) | Acoustic liner for air-inlet nacelle of aircraft engine and aircraft engine | |
| CN109236496A (en) | The three power combination engine design methods that Asia combustion can be switched with super burn channel | |
| CN105157947B (en) | A kind of combination in series power air intake duct MODAL TRANSFORMATION OF A test method | |
| EP2971727B1 (en) | Asymmetric fan nozzle in high-bpr separate-flow nacelle | |
| GB1289906A (en) | ||
| CN108844708B (en) | Injection type nacelle sonic nozzle combination arrangement method | |
| CN209083430U (en) | The turbofan punching press combined engine of rocket built in a kind of outer culvert | |
| Magrini et al. | Analysis of ultra-high bypass ratio turbofan nacelle geometries with conventional and short intakes at take-off and cruise | |
| CN109458274B (en) | Variable cross-section petal-shaped injection mixer suitable for pulse detonation engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |