CN109060293A - A method of improving injection type nacelle charge flow rate - Google Patents
A method of improving injection type nacelle charge flow rate Download PDFInfo
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- CN109060293A CN109060293A CN201811053680.8A CN201811053680A CN109060293A CN 109060293 A CN109060293 A CN 109060293A CN 201811053680 A CN201811053680 A CN 201811053680A CN 109060293 A CN109060293 A CN 109060293A
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- Prior art keywords
- nacelle
- injection type
- flow rate
- water conservancy
- conservancy diversion
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- 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
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- 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 kind of methods for improving injection type nacelle charge flow rate, the injection type nacelle includes nacelle inlet, nacelle wall surface and nacelle outlet, it is provided with several groups sonic nozzle in the injection type nacelle, flow-guiding structure from inside to outside is provided on the nacelle wall；The present invention is by arranging water conservancy diversion grid in injection nacelle outlet upstream, and flow deflector is set and is exported part high-speed jet and low speed to nacelle tail portion by the mixed airflow of injection air-flow, convergence type jet pipe bring congestion effect is reduced, the charge flow rate of injection nacelle can be significantly improved.
Description
Technical field
The present invention relates to experimental aerodynamics fields, more particularly, to a kind of side for improving injection type nacelle charge flow rate
Method.
Background technique
In order to study influence of the turbofan aircraft engine intake and exhaust to aircraft aerodynamic characteristic, need to carry out power in wind-tunnel
Simulation test, injection type nacelle are one of analog forms.Injection type nacelle is the simulator of fanjet in wind-tunnel, is used
In influence of the simulated engine intake and exhaust to aircraft aerodynamic characteristic.Injection type nacelle uses high pressure air drives, it passes through velocity of sound
Pressure-air is injected into inside nacelle by nozzle, generates high-speed jet, under the ejector action of high-speed jet, the air of surrounding by
Nacelle inlet enters nacelle and generates flowing, forms low speed and is filled by injection air-flow, high-speed jet and low speed by injection air-flow
After dividing mixing, exports and be discharged through nacelle, see Fig. 1.Injection type nacelle charge flow rate is the important finger of injection type nacelle analog capability
Mark.However injection type nacelle generallys use convergence type jet pipe, (is greater than 1.5) when injection nacelle outlet blow down ratio is higher, high speed
Jet stream and low speed produce congestion effect in nacelle exit by injection air-flow, and nacelle intake simulation ability is caused to strongly reduce,
When injection nacelle outlet blow down ratio further increase when, nacelle inlet even will appear refluence, seriously affect injection type nacelle into
Gas simulates effect.
Summary of the invention
The purpose of the present invention is in view of the above-mentioned problems, proposing a kind of method for improving injection type nacelle charge flow rate, solution
Convergence type jet pipe bring congestion effect improves charge flow rate.
To achieve the goals above, the present invention adopts the following technical scheme:
A method of injection type nacelle charge flow rate being improved, the injection type nacelle includes nacelle inlet, nacelle wall surface and short
Cabin exports, and is provided with several groups sonic nozzle in the injection type nacelle, water conservancy diversion from inside to outside is provided on the nacelle wall
Structure.
In the above-mentioned technical solutions, the flow-guiding structure includes the water conservancy diversion grid being arranged on nacelle wall and is arranged short
Flow deflector on the inner wall of cabin.
In the above-mentioned technical solutions, the water conservancy diversion grid is arranged on the nacelle wall surface tail portion of nacelle outlet.
In the above-mentioned technical solutions, no less than four groups of water conservancy diversion grid, each group of water conservancy diversion are provided on the nacelle wall surface
Grid can be dismounted independently.
In the above-mentioned technical solutions, the water conservancy diversion grid of multiple groups is evenly distributed in the same of the nacelle wall surface of injection type nacelle
On circumference.
In the above-mentioned technical solutions, free closing may be implemented in described each group of water conservancy diversion grid.
In the above-mentioned technical solutions, all groups of water conservancy diversion grid can be applied in combination between each other, realize different water conservancy diversion
Mode.
In the above-mentioned technical solutions, the flow deflector is arranged on nacelle inner wall, is located at nacelle outlet upstream position, uses
In part high-speed jet and low speed are branched to water conservancy diversion grid by the mixed airflow of injection air-flow.
In the above-mentioned technical solutions, the several groups sonic nozzle is evenly distributed on same periphery.
In the above-mentioned technical solutions, the several groups sonic nozzle constitutes the annulus permutation of different radii except interior.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
Flow deflector is arranged by part high-speed jet and low speed by arranging water conservancy diversion grid in injection nacelle outlet upstream in the present invention
It is exported by the mixed airflow of injection air-flow to nacelle tail portion, reduces convergence type jet pipe bring congestion effect, can significantly mention
The charge flow rate of high injection nacelle.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1, Fig. 2 are injection nacelle structure schematic diagram；
Wherein: 1 is nacelle inlet, and 2 be sonic nozzle, and 3 be nacelle outlet, and 4 be water conservancy diversion grid, and 5 be flow deflector.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Injection type nacelle uses high pressure air drives, and pressure-air is injected into inside nacelle by it by sonic nozzle, produces
Raw high-speed jet, under the ejector action of high-speed jet, the air of surrounding enters nacelle by nacelle inlet and generates flowing, is formed
After low speed is sufficiently mixed by injection air-flow, high-speed jet and low speed by injection air-flow, exports and exclude through nacelle, see Fig. 1.
The method of the raising injection type nacelle charge flow rate is located at the upstream position installation of nacelle outlet in nacelle inner wall
Flow deflector, by part high-speed jet and low speed branches to water conservancy diversion grid by the mixed airflow of injection air-flow.Part high-speed jet
It is exported using water conservancy diversion grid to nacelle tail portion with low speed by the mixed airflow of injection air-flow.The mixed airflow that this part is split
So that reducing by the air flow rate that nacelle exports, convergence type jet pipe bring congestion effect is reduced, so that it is short to improve injection
The charge flow rate in cabin.Mixed gas is divided into multiple jets by water conservancy diversion grid, by optimization grating position and grid parameter (angle,
Type face etc.) multiple jets can be mixed with the main jet stream by nacelle outlet again, so that by-pass shunt is pneumatic to aircraft
The influence of characteristic minimizes.
Water conservancy diversion grid can be applied in combination, and flexibly and easily, expansibility is strong.Arrange that multiple groups (are more than or equal to 4 in nacelle surrounding
Group) water conservancy diversion grid, every group can independently dismount, and see Fig. 2.In actual use, can be according to model aircraft the characteristics of, targetedly closes
The water conservancy diversion grid in certain directions is closed, flexibly and easily, expansibility is strong.If certain aircraft engine nacelle is mounted below wing, by
Close apart from wing position in nacelle, the air-flow of the water conservancy diversion grid discharge on nacelle top may directly be flow on wing, right
Wing generates active force, it will additional error is brought to dynamic simulation trial result, therefore, the characteristics of according to the aircraft,
Just the water conservancy diversion grid on nacelle top is closed when designing the injection type nacelle, and nacelle side and following water conservancy diversion grid are protected
It stays, to improve the performance of injection type nacelle, and eliminates the extra error of dynamic simulation trial result.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (10)
1. it is a kind of improve injection type nacelle charge flow rate method, the injection type nacelle include nacelle inlet, nacelle wall surface and
Nacelle outlet, it is characterised in that several groups sonic nozzle is provided in the injection type nacelle, be provided on the nacelle wall from
It is interior to arrive outer flow-guiding structure.
2. a kind of method for improving injection type nacelle charge flow rate according to claim 1, it is characterised in that the water conservancy diversion
Structure includes the water conservancy diversion grid being arranged on nacelle wall and the flow deflector being arranged on nacelle inner wall.
3. a kind of method for improving injection type nacelle charge flow rate according to claim 2, it is characterised in that the water conservancy diversion
Grid is arranged on the nacelle wall surface tail portion of nacelle outlet.
4. a kind of method for improving injection type nacelle charge flow rate according to claim 3, it is characterised in that the nacelle
No less than four groups of water conservancy diversion grid is provided on wall surface, each group of water conservancy diversion grid can be dismounted independently.
5. a kind of method for improving injection type nacelle charge flow rate according to claim 4, it is characterised in that multiple groups are led
On the same circumference for the nacelle wall surface that stream grid is evenly distributed in injection type nacelle.
6. a kind of method for improving injection type nacelle charge flow rate according to claim 4, it is characterised in that described each
Free closing may be implemented in the water conservancy diversion grid of group.
7. a kind of method for improving injection type nacelle charge flow rate according to claim 5, it is characterised in that all groups
Water conservancy diversion grid can be applied in combination between each other, realize different water conservancy diversion modes.
8. a kind of method for improving injection type nacelle charge flow rate according to claim 2, it is characterised in that the water conservancy diversion
Piece is arranged on nacelle inner wall, is located at nacelle outlet upstream position, is used for part high-speed jet and low speed by injection air-flow
Mixed airflow branch to water conservancy diversion grid.
9. a kind of method for improving injection type nacelle charge flow rate according to claim 1, it is characterised in that described several
Group sonic nozzle is evenly distributed on same periphery.
10. a kind of method for improving injection type nacelle charge flow rate according to claim 9, it is characterised in that described several
Group sonic nozzle constitutes the annulus permutation of different radii except interior.
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 true CN109060293A (en) | 2018-12-21 |
| CN109060293B CN109060293B (en) | 2020-07-28 |
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| 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 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650791A (en) * | 2021-09-08 | 2021-11-16 | 中国商用飞机有限责任公司 | Nacelle and aircraft equipped with same |
| CN113942630A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Airfoil surface for generating lift force and thrust force based on airflow ejection effect and aircraft |
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 |
|---|
| 章荣平 等: "低速风洞引射短舱动力模拟技术新进展", 《空气动力学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650791A (en) * | 2021-09-08 | 2021-11-16 | 中国商用飞机有限责任公司 | Nacelle and aircraft equipped with same |
| CN113942630A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Airfoil surface for generating lift force and thrust force based on airflow ejection effect and aircraft |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109060293B (en) | 2020-07-28 |
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