CN204436596U - A kind of pressed engine radial air inlet distortion suppresses grid - Google Patents
A kind of pressed engine radial air inlet distortion suppresses grid Download PDFInfo
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- CN204436596U CN204436596U CN201520112997.XU CN201520112997U CN204436596U CN 204436596 U CN204436596 U CN 204436596U CN 201520112997 U CN201520112997 U CN 201520112997U CN 204436596 U CN204436596 U CN 204436596U
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Abstract
A kind of pressed engine radial air inlet distortion suppresses grid, relates to pressed engine.Being provided with the first distortion suppresses grid sheet and the second distortion to suppress grid sheet, first distortion suppresses grid sheet and the second distortion to suppress grid sheet coaxial layers to stack, described first distortion suppresses grid sheet to be made up of around central cylinder flexible screw sheet, can be furled by actuating motor or roll up and put the central cylinder realization control flexible screw sheet number of turns, second distortion suppresses grid sheet to be made up of the radial vertically hung scroll of fixed qty, second distortion suppresses grid sheet to maintain static relative to pressed engine geometric position, first distortion suppresses grid sheet and the second distortion to suppress grid sheet to be installed on pressed engine circular chamber entrance.Structure is simple, control is convenient, greatly improves the anti-radial distortion ability of pressed engine, increases engine stabilizer margin of operation.
Description
Technical field
The utility model relates to pressed engine, especially relates to the distortion of a kind of pressed engine radial air inlet and suppresses grid.
Background technique
Pressed engine belongs to air-inlet type propelled at high velocity power plant, is widely used in the high-speed aircrafts such as supersonic cruising guided missile and supersonic aircraft, for it provides jet propulsion power.Conventional punch motor is made up of three large critical pieces, is Diffuser, firing chamber and jet pipe respectively.First high velocity air enters Diffuser deceleration diffusion, and speed drops to subsonic velocity by ultrasound velocity, subsequently ignition in a combustion chamber, and finally from jet pipe, ejection produces thrust.
From pressed engine parts, diffuser exit air-flow will enter combustion chamber ignition burning, and under true environment, diffuser exit air-flow is difficult to the uniformity ensureing pressure and velocity distribution in three dimensional space, namely occurs what is called " distortion ".Flow distortion degree due to entry of combustion chamber has a strong impact on the blending in a combustion chamber of air-flow and fuel and smooth combustion, therefore measure diffuser exit air-flow being taked to rectification homogenization is necessary, make to enter the space distribution uniformity as far as possible of stream pressure in firing chamber and speed, to ensure to obtain good firing effect and more preferably pressed engine thrust, the process of uniform stream is " distortion suppression ".
At present, in existing a large amount of inlet distortion braking measure, air-inlet grille obtains and uses the most widely and achieved gratifying distortion inhibition.But the grid that in current air-inlet grille design proposal, substantially all single, the geometric format of different forms is fixing, all remains unchanged at the hole shape of motor different operating state Under The Grille, pore size, congestion degree.The distortion of fixing geometric format suppresses grid to be difficult to ensure all to obtain under motor all working state good flow distortion inhibition engine interior aerodynamical resistance minimally simultaneously.Therefore, the inlet distortion that geometry is adjustable suppresses grid to be desirable selection for the pressed engine of wide range work.
Summary of the invention
Technical problem to be solved in the utility model is to overcome prior art defect, provides and can control pressed engine at different flight attitude and the adjustable a kind of pressed engine radial air inlet distortion suppression grid of flight environment lower combustion chamber entrance radial distortion suppression degree.
The utility model is provided with the first distortion and suppresses grid sheet and the second distortion to suppress grid sheet, first distortion suppresses grid sheet and the second distortion to suppress grid sheet coaxial layers to stack, described first distortion suppresses grid sheet to be made up of around central cylinder flexible screw sheet, can be furled by actuating motor or roll up and put the central cylinder realization control flexible screw sheet number of turns, second distortion suppresses grid sheet to be made up of the radial vertically hung scroll of fixed qty, second distortion suppresses grid sheet to maintain static relative to pressed engine geometric position, first distortion suppresses grid sheet and the second distortion to suppress grid sheet to be installed on pressed engine circular chamber entrance.
The utility model can adopt following methods to design:
1) determine maximum radial distortion value DIS_R according to different aircraft inlet flow conditions by wind-tunnel flyoff or numerical value emulation method, DIS_R is determined by following formula:
In formula,
for entry of combustion chamber average total pressure,
for circular cross-section ingress, firing chamber accounts for minimum value in the annulus average total pressure of the area of a circle 1/10, ρ
∞for freely carrying out current density, U
∞for free speed of incoming flow;
2) determine to suppress the smallest circle anchor ring needed for this maximum radial distortion value DIS_R to amass AR by wind-tunnel flyoff or numerical value emulation method
min.
3) determine that the first distortion suppresses the screw piece number of turns of grid sheet, the screw piece number of turns is that firing chamber circular chamber entrance circular area is divided by AR
min;
4) determine that the second distortion suppresses the radial vertically hung scroll quantity of grid sheet, radial vertically hung scroll quantity is 3 times that the first distortion suppresses the screw piece number of turns of grid sheet.
Working method of the present utility model is:
When aircraft takes off from ground, the first distortion suppresses the screw piece retracting of grid sheet, makes the number of turns be 1/2 of the design point screw piece number of turns;
When aircraft large attack angle climbing flight or high angles of side slip flight, the first distortion suppresses the screw piece of grid sheet volume to be put, and makes the number of turns be the design point screw piece number of turns;
When vehicle flight speeds reaches that after cruising speed, the angle of attack and angle of sideslip are down to design point, the first distortion suppresses the screw piece retracting of grid sheet, makes the number of turns be 1/2 of the design point screw piece number of turns;
Cause angle of attack angle of sideslip to increase when aircraft average flight state is interfered, the first distortion suppresses the screw piece of grid sheet volume to be put, and makes the number of turns be the design point screw piece number of turns;
When the descending flight of aircraft large attack angle or high angles of side slip flight, the first distortion suppresses the screw piece of grid sheet volume to be put, and makes the number of turns be the design point screw piece number of turns.
The utility model by volume put the first distortion suppress grid sheet flexible screw sheet increase the number of turns realize pressed engine large attack angle and high angles of side slip flight attitude under radial distortion effectively suppress, furl the first distortion simultaneously when pressed engine runs with normal flight attitude and suppress the grid sheet flexible screw sheet minimizing number of turns to reduce pressed engine internal aero-drag.
Working principle of the present utility model is: the radial air inlet distortion of installing geometry adjustable at conventional punch motor circular cross-section entry of combustion chamber suppresses grid, change the different corresponding adjustment distortion of the diffuser exit air-flow radial distortion degree caused according to the regime of flight of aircraft and suppress grid diametric(al) pore-size distribution density, the radial distortion reducing diffuser exit air-flow obtains minimum internal aero-drag simultaneously, help propulsion system to obtain best propulsive efficiency, be mainly used in pressed engine.When pressed engine is in take-off climb stage, decline stage or when working with large attack angle high angles of side slip flight attitude, there is nonuniformity in a big way in space distribution in entry of combustion chamber airspeed and pressure, becomes difficulty after causing air-flow to enter scramjet combustor with the blending of fuel and smooth combustion.In order to suppress the radial distortion of scramjet combustor inlet air flow, volume is put distortion and is suppressed grid sheet variable partition, reduce the sparse degree that the overall hole of grid diametrically distributes, make air-flow pass closeer grid thus the radial nonuniformity of reduction air-flow; Otherwise, when pressed engine is in cruising condition or with Low Angle Of Attack, the work of little angle of sideslip flight attitude, retracting distortion suppresses grid variable partition, increase the overall hole of grid sparse degree diametrically, make air-flow pass relatively sparse grid thus reduce pressed engine internal aero-drag.
The beneficial effects of the utility model are: (1), by rotate volume put realize pressed engine large attack angle and high angles of side slip flight attitude under radial distortion effectively suppress, when pressed engine runs with normal flight attitude, volume is put the first distortion and is suppressed grid sheet flexible screw sheet to increase distortion to suppress the overall sparse degree reduction internal aero-drag of grid simultaneously; (2), its structure of the utility model is simple, control is convenient, greatly improves the anti-radial distortion ability of pressed engine, increases engine stabilizer margin of operation.
Accompanying drawing explanation
Fig. 1 is the utility model embodiment mounting point schematic diagram in pressed engine;
Fig. 2 is the utility model embodiment mounting point front view in pressed engine;
Fig. 3 is the utility model embodiment rigging position schematic diagram;
Fig. 4 is the utility model embodiment unitary side view assembled;
Fig. 5 is that the first distortion suppresses the overall front view of the screw piece rolled condition grid of grid sheet;
Fig. 6 is that the first distortion suppresses the screw piece of grid sheet volume to put the overall front view of state grid.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As shown in figs. 1 to 6, the utility model is installed in pressed engine internal flow channel, and conventional punch motor is made up of Diffuser 1, firing chamber 2 and jet pipe 3, and wherein, firing chamber 2 entrance section is circular.The utility model (representing with mark 4 in fig 1 and 2) is installed on ingress, firing chamber 2.
The utility model embodiment is provided with the first distortion and suppresses grid sheet 5 and the second distortion to suppress grid sheet 6, first distortion suppresses grid sheet 5 and the second distortion to suppress grid sheet 6 coaxial layers to stack, described first distortion suppresses grid sheet 5 to be made up of around central cylinder flexible screw sheet, can be furled by actuating motor or roll up and put the central cylinder realization control flexible screw sheet number of turns, second distortion suppresses grid sheet 6 to be made up of the radial vertically hung scroll of fixed qty, second distortion suppresses grid sheet 6 to maintain static relative to pressed engine geometric position, first distortion suppresses grid sheet 5 and the second distortion to suppress grid sheet 6 to be installed on pressed engine circular chamber 2 entrance.
Design method of the present utility model, comprises the following steps:
1) determine maximum radial distortion value DIS_R according to different aircraft inlet flow conditions by wind-tunnel flyoff or numerical value emulation method, DIS_R is determined by following formula:
In formula,
for entry of combustion chamber average total pressure,
for circular cross-section ingress, firing chamber accounts for minimum value in the annulus average total pressure of the area of a circle 1/10, ρ
∞for freely carrying out current density, U
∞for free speed of incoming flow.
2) determine to suppress the smallest circle anchor ring needed for this maximum radial distortion value DIS_R to amass AR by wind-tunnel flyoff or numerical value emulation method
min.
3) determine that the first distortion suppresses the screw piece number of turns of grid sheet, the screw piece number of turns is that firing chamber circular chamber entrance circular area is divided by AR
min.
4) determine that the second distortion suppresses the radial vertically hung scroll quantity of grid sheet, radial vertically hung scroll quantity is 3 times that the first distortion suppresses the screw piece number of turns of grid sheet.
The working method of described pressed engine radial air inlet distortion suppression grid is:
When aircraft takes off from ground, the first distortion suppresses the screw piece retracting of grid sheet, makes the number of turns be 1/2 of the design point screw piece number of turns;
When aircraft large attack angle climbing flight or high angles of side slip flight, the first distortion suppresses the screw piece of grid sheet volume to be put, and makes the number of turns be the design point screw piece number of turns;
When vehicle flight speeds reaches that after cruising speed, the angle of attack and angle of sideslip are down to design point, the first distortion suppresses the screw piece retracting of grid sheet, makes the number of turns be 1/2 of the design point screw piece number of turns;
Cause angle of attack angle of sideslip to increase when aircraft average flight state is interfered, the first distortion suppresses the screw piece of grid sheet volume to be put, and makes the number of turns be the design point screw piece number of turns;
When the descending flight of aircraft large attack angle or high angles of side slip flight, the first distortion suppresses the screw piece of grid sheet volume to be put, and makes the number of turns be the design point screw piece number of turns.
The utility model by volume put the first distortion suppress grid sheet flexible screw sheet increase the number of turns realize pressed engine large attack angle and high angles of side slip flight attitude under radial distortion effectively suppress, furl the first distortion simultaneously when pressed engine runs with normal flight attitude and suppress the grid sheet flexible screw sheet minimizing number of turns to reduce pressed engine internal aero-drag.
Working principle of the present utility model is: the radial air inlet distortion of installing geometry adjustable at conventional punch motor circular cross-section entry of combustion chamber suppresses grid, change the different corresponding adjustment distortion of the diffuser exit air-flow radial distortion degree caused according to the regime of flight of aircraft and suppress grid diametric(al) pore-size distribution density, the radial distortion reducing diffuser exit air-flow obtains minimum internal aero-drag simultaneously, help propulsion system to obtain best propulsive efficiency, be mainly used in pressed engine.When pressed engine is in take-off climb stage, decline stage or when working with large attack angle high angles of side slip flight attitude, there is nonuniformity in a big way in space distribution in entry of combustion chamber airspeed and pressure, becomes difficulty after causing air-flow to enter scramjet combustor with the blending of fuel and smooth combustion.In order to suppress the radial distortion of scramjet combustor inlet air flow, volume is put distortion and is suppressed grid sheet variable partition, reduce the sparse degree that the overall hole of grid diametrically distributes, make air-flow pass closeer grid thus the radial nonuniformity of reduction air-flow; Otherwise, when pressed engine is in cruising condition or with Low Angle Of Attack, the work of little angle of sideslip flight attitude, retracting distortion suppresses grid variable partition, increase the overall hole of grid sparse degree diametrically, make air-flow pass relatively sparse grid thus reduce pressed engine internal aero-drag.
Design method detailed process of the present utility model is:
First, determine maximum radial distortion value DIS_R according to different aircraft inlet flow conditions by wind-tunnel flyoff or numerical value emulation method, DIS_R is determined by following formula;
in formula,
for entry of combustion chamber average total pressure,
circular cross-section ingress, firing chamber accounts for minimum value in the annulus average total pressure of the area of a circle 1/10, ρ
∞for freely carrying out current density, U
∞for free speed of incoming flow;
Secondly, determine to suppress the smallest circle anchor ring needed for this maximum radial distortion value DIS_R to amass AR by wind-tunnel flyoff or numerical value emulation method
min;
Then, determine that the first distortion suppresses the screw piece number of turns of grid sheet, the screw piece number of turns is that firing chamber circular chamber entrance circular area is divided by AR
min;
Finally, determine that the second distortion suppresses the radial vertically hung scroll quantity of grid sheet, grid radius vertically hung scroll quantity is 3 times that the first distortion suppresses the grid sheet spiral number of turns.
Working method of the present utility model comprises following process:
When aircraft takes off from ground, the first distortion suppresses the retracting of grid sheet 5 screw piece, makes the number of turns be 1/2 of the design point screw piece number of turns, and after retracting, the overall front view of grid as shown in Figure 5.
When aircraft large attack angle climbing flight or high angles of side slip flight, the first distortion suppresses grid sheet 5 screw piece volume to be put, and makes the number of turns be the design point screw piece number of turns, and volume puts the overall front view of rear grid as shown in Figure 6.
When vehicle flight speeds reaches that after cruising speed, the angle of attack and angle of sideslip are down to design point, the first distortion suppresses the retracting of grid sheet 5 screw piece, makes the number of turns be 1/2 of the design point screw piece number of turns, and after retracting, the overall front view of grid as shown in Figure 5.
Cause angle of attack angle of sideslip to increase when aircraft average flight state is interfered, the first distortion suppresses grid sheet 5 screw piece volume to be put, and makes the number of turns be the design point screw piece number of turns, and volume puts the overall front view of rear grid as shown in Figure 6;
When the descending flight of aircraft large attack angle or high angles of side slip flight, the first distortion suppresses grid sheet 5 screw piece volume to be put, and makes the number of turns be the design point screw piece number of turns, and volume puts the overall front view of rear grid as shown in Figure 6.
Claims (1)
1. a pressed engine radial air inlet distortion suppresses grid, it is characterized in that being provided with the first distortion suppresses grid sheet and the second distortion to suppress grid sheet, first distortion suppresses grid sheet and the second distortion to suppress grid sheet coaxial layers to stack, described first distortion suppresses grid sheet to be made up of around central cylinder flexible screw sheet, furled by actuating motor or roll up and put the central cylinder realization control flexible screw sheet number of turns, second distortion suppresses grid sheet to be made up of the radial vertically hung scroll of fixed qty, second distortion suppresses grid sheet to maintain static relative to pressed engine geometric position, first distortion suppresses grid sheet and the second distortion to suppress grid sheet to be installed on pressed engine circular chamber entrance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520112997.XU CN204436596U (en) | 2015-02-16 | 2015-02-16 | A kind of pressed engine radial air inlet distortion suppresses grid |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520112997.XU CN204436596U (en) | 2015-02-16 | 2015-02-16 | A kind of pressed engine radial air inlet distortion suppresses grid |
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| Publication Number | Publication Date |
|---|---|
| CN204436596U true CN204436596U (en) | 2015-07-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520112997.XU Withdrawn - After Issue CN204436596U (en) | 2015-02-16 | 2015-02-16 | A kind of pressed engine radial air inlet distortion suppresses grid |
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| Country | Link |
|---|---|
| CN (1) | CN204436596U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104615838A (en) * | 2015-02-16 | 2015-05-13 | 厦门大学 | Radial air inlet distortion restraining grating of ramjet engine and designing method of radial air inlet distortion restraining grating |
-
2015
- 2015-02-16 CN CN201520112997.XU patent/CN204436596U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104615838A (en) * | 2015-02-16 | 2015-05-13 | 厦门大学 | Radial air inlet distortion restraining grating of ramjet engine and designing method of radial air inlet distortion restraining grating |
| CN104615838B (en) * | 2015-02-16 | 2017-05-24 | 厦门大学 | Radial air inlet distortion restraining grating of ramjet engine and designing method of radial air inlet distortion restraining grating |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150701 Effective date of abandoning: 20170524 |
|
| AV01 | Patent right actively abandoned |