CN209410346U - Bleed radiator - Google Patents
Bleed radiator Download PDFInfo
- Publication number
- CN209410346U CN209410346U CN201821958553.8U CN201821958553U CN209410346U CN 209410346 U CN209410346 U CN 209410346U CN 201821958553 U CN201821958553 U CN 201821958553U CN 209410346 U CN209410346 U CN 209410346U
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- bleed
- ejector pipe
- heat shield
- connector
- engine
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Abstract
The utility model provides a kind of bleed radiator, belongs to technical field of aerospace, engine nacelle temperature excessively high technical problem when solving existing unmanned plane high-speed flight.The device includes ejector pipe and heat shield, the heat shield is fixed in rear body, the ejector pipe is fixed in the heat shield and is equipped with gap between the side wall of the two to form drainage channel, the air intake duct of unmanned plane is communicated with the air inlet of engine and the part cold airflow of air intake duct outflow is by generating combustion gas after the engine, the jet pipe of the engine be connected with the ejector pipe and the combustion gas that is sprayed through the jet pipe through the ejector pipe injection to engine nacelle outside, the part cold airflow of the air intake duct outflow, which can flow into the drainage channel and the ejector pipe, is thermally shielded cooling with the combustion gas sprayed to the jet pipe.
Description
Technical field
The utility model relates to technical field of aerospace, more particularly, to a kind of bleed radiator.
Background technique
Unmanned plane supplies gas to engine by air intake duct so that engine does work, during high-speed flight, after being set to
The engine moment of fuselage is in running order, and sprays high-temperature fuel gas from jet pipe and generate thrust, since jet pipe sprays
Fuel gas temperature up to thousands of degree, cause temperature in engine nacelle excessively high, rear body nearby be also equipped with other systems or set
Standby, such high temperature has exceeded the normal working temperature of engine accessory power rating and other equipment, if can make without heat-insulated cooling provision
Engine accessory power rating and other system or equipments can not work normally, and influence service life.
Utility model content
The purpose of this utility model is to provide a kind of bleed radiator, hair when solving existing unmanned plane high-speed flight
The excessively high technical problem of motivation cabin temperature.Optimal technical scheme in many technical solutions provided by the utility model can produce
Raw many technical effects elaboration as detailed below.
To achieve the above object, the utility model provides following technical scheme:
The utility model provides a kind of bleed radiator, including ejector pipe and heat shield, and the heat shield is fixed on
In rear body, the ejector pipe is fixed in the heat shield and is equipped with gap between the side wall of the two to form drainage channel,
The air intake duct of unmanned plane is communicated with the air inlet of engine and the part cold airflow of air intake duct outflow passes through the engine
After generate combustion gas, the jet pipe of the engine be connected with the ejector pipe and the combustion gas warp that is sprayed through the jet pipe described in
Outside ejector pipe injection to engine nacelle, the part cold airflow of air intake duct outflow can flow into the drainage channel and described
Cooling is thermally shielded with the combustion gas sprayed to the jet pipe in ejector pipe.
Preferably, the ejector pipe includes the first bleed section and the first gas collecting segment, first gas collecting segment and described first
The end to end formation trumpet type of bleed section and the diameter of the free end of first gas collecting segment are greater than oneself of the first bleed section
By the diameter held.
Preferably, the heat shield includes the second gas collecting segment and the second bleed section, second gas collecting segment and described second
The end to end formation trumpet type of the bleed section and heat shield is identical as the ejector pipe axis.
Preferably, the second bleed section is equal with the first bleed segment length, and the axis of second gas collecting segment is long
Degree is greater than the axial length of first gas collecting segment.
Preferably, injection section is extended in the free end of the second bleed section, the shape of the free end of the injection section with
The rear body is adapted.
Preferably, second gas collecting segment offers at least two ventholes close to described engine one end.
Preferably, the ejector pipe is fixedly connected with the heat shield by connector.
Preferably, the connector includes the first connector and/or the second connector, and first connector is set to institute
One end of ejector pipe minor diameter is stated, second connector is set to one end of the ejector pipe major diameter.
Preferably, first connector is U-shaped part, and second connector is Z-type part.
Preferably, the distance between the ejector pipe and the heat shield are 15mm~30mm.
The utility model relates to a kind of bleed radiators to have the following beneficial effects: compared with prior art
The bleed radiator being made of ejector pipe and heat shield is arranged in the utility model in rear body, can be by jet pipe
The high-temperature fuel gas of ejection through ejector pipe injection to engine nacelle outside, be provided between ejector pipe and heat shield tap air channel with
Make between jet pipe and ejector pipe, form dual insulated space between ejector pipe and heat shield, part cold airflow is made to pass through bleed
In channel and ejector pipe, the aggregation of heat is avoided, heat transmitting is reduced, reduces the temperature of ejector pipe, make the heat of high-temperature fuel gas
Amount does not diffuse into engine nacelle, and the utility model has the function of, cooling heat-insulated to high-temperature fuel gas, avoids due to hair
In motivation cabin temperature it is excessively high and the drawbacks of damage other parts or electronic component.
Detailed description of the invention
It, below will be to description of the prior art in order to illustrate more clearly of the utility model or technical solution in the prior art
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model
Embodiment for those of ordinary skill in the art without creative efforts, can also be attached according to these
Figure obtains other attached drawings.
Fig. 1 is the structural schematic diagram that the utility model is set in unmanned plane；
Fig. 2 is the structural schematic diagram of the utility model；
Fig. 3 is that the utility model passes through the fixed structural schematic diagram of the first connector；
Fig. 4 is the structural schematic diagram of first connector of the utility model；
Fig. 5 is the structural schematic diagram of second connector of the utility model；
1, ejector pipe in figure；11, the first bleed section；12, the first gas collecting segment；2, heat shield；21, the second bleed section；22,
Two gas collecting segments；23, injection section；24, venthole；3, engine；4, jet pipe；5, air intake duct；6, rear body；7, the first connection
Part；8, the second connector.
Specific embodiment
To keep the purpose of this utility model, technical solution and advantage clearer, below by the technology to the utility model
Scheme is described in detail.Obviously, the described embodiments are only a part of the embodiments of the utility model, rather than all
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are not before making creative work
Obtained all other embodiment is put, the range that the utility model is protected is belonged to.
In the description of the present invention, it should be understood that term " center ", " lateral ", " length ", " width ", " height
Degree ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " side " etc. refer to
The orientation or positional relationship shown be based on orientation or positional relationship shown in FIG. 1, be merely for convenience of description the utility model and
Simplify description, rather than the equipment of indication or suggestion meaning or element must have a particular orientation, with specific orientation construction
And operation, therefore should not be understood as limiting the present invention.
As shown in Figure 1, the utility model provides a kind of bleed radiator, including ejector pipe 1 and heat shield 2, it is heat-insulated
Cover 2 is fixed in rear body 6, and ejector pipe 1 is fixed in heat shield 2 and is equipped with gap between the side wall of the two to be led to forming drainage
The part cold airflow that the air intake duct 5 in road, unmanned plane is communicated with the air inlet of engine 3 and air intake duct 5 flows out passes through after engine 3
High-temperature fuel gas is generated, the jet pipe 4 of engine 3 is connected with ejector pipe 1 and the combustion gas sprayed through jet pipe 4 is drawn through ejector pipe 1
It is incident upon 3 nacelle exterior of engine, the part cold airflow that air intake duct 5 flows out can flow into drainage channel and ejector pipe 1 to spray to tail
The combustion gas that pipe 4 sprays is thermally shielded cooling.
Wherein, air intake duct 5 communicated with the air inlet of engine 3 specific connection type can with no restrictions, as long as guarantee air inlet
The cold airflow in road 5 largely enters in engine 3 and generates high-temperature fuel gas, and small part flows into bleed radiator, this reality
Applying example is the air inlet that air intake duct 5 is located at engine 3；The jet pipe 4 of engine 3 is connected with ejector pipe 1 refers to guarantee tail spray
The high-temperature fuel gas that pipe 4 sprays can be entered ejector pipe 1 by injection, and jet pipe 4 protrudes into ejector pipe 1 in the present embodiment；Heat shield 2
It using glass-reinforced plastic material, prevents heat radiation from spreading, reduces heat transmitting；1 material of ejector pipe uses stainless steel material, by high-temperature fuel gas
It is confined in ejector pipe 1.
The bleed radiator being made of ejector pipe 1 and heat shield 2 is arranged in the utility model in rear body 6, can be by tail
The high-temperature fuel gas that jet pipe 4 sprays, to 3 nacelle exterior of engine, is provided with through 1 injection of ejector pipe between ejector pipe 1 and heat shield 2
Tap air channel forms dual insulated space, makes part so that between jet pipe 4 and ejector pipe 1 between ejector pipe 1 and heat shield 2
Cold airflow is by avoiding the aggregation of heat, reducing the temperature of ejector pipe 1, make high-temperature fuel gas in tap air channel and ejector pipe 1
Heat do not diffuse into 3 cabin of engine, the utility model have the function of it is heat-insulated to high-temperature fuel gas, cooling, avoid
Due in 3 cabin of engine temperature it is excessively high and the drawbacks of damage other parts or electronic component.
As optional embodiment, as shown in Fig. 2, ejector pipe 1 includes the first bleed section 11 and the first gas collecting segment 12, the
One gas collecting segment 12 and the first bleed section 11 is end to end forms trumpet type and the diameter of the free end of the first gas collecting segment 12 is greater than institute
State the diameter of the free end of the first bleed section 11.
Specifically, the length of the first bleed section 11 is greater than the length of the first gas collecting segment 12, the flared of the first gas collecting segment 12
Structure facilitates protruding into and being conducive to the collection to cold airflow for jet pipe 4；When unmanned plane high-speed flight, air-flow passes through one end diameter
The small convergent contour channel meeting speedup of big one section of diameter, the air velocity sprayed by ejector pipe 1 is bigger, and reaction thrust is also got over
Greatly, reduce unmanned plane during flying when resistance and be conducive to speedup.
As optional embodiment, heat shield 2 includes the second gas collecting segment 22 and the second bleed section 21, the second gas collecting segment 22
With the end to end formation trumpet type of the second bleed section 21 and heat shield 2 it is identical as 1 axis of ejector pipe.
Second gas collecting segment 22 and the second bleed section 21, which form trumpet type, ensure that structure similar with ejector pipe 1, be conducive to pair
The collection of the cold airflow of air intake duct 5, while cold airflow enters the first gas collecting segment 12 after heat shield 2 and receives to part cold airflow
Collection makes have cold airflow circulation in ejector pipe 1 and in drainage channel, conducive to the heat insulation and heat control to high-temperature fuel gas, meanwhile, heat shield 2
And the Structure adaptation that with high-temperature fuel gas injection direction radical length is gradually reduced close with 1 structure of ejector pipe unmanned plane rear body
6 shape, reduces resistance, is conducive to high-speed flight；The spacing for making drainage channel identical as 1 axis of ejector pipe of heat shield 2 is uniform,
The present embodiment is 15mm~30mm, ensure that effective heat-insulated cooling distance, avoiding makes ejector pipe 1 and heat shield apart from too small
Heat-insulated cooling effect caused by 2 hypotelorisms is undesirable, and apart from excessive taken up space excessive drawback.
As optional embodiment, 11 equal length of the second bleed section 21 and the first bleed section, the second gas collecting segment 22
Axial length is greater than the axial length of the first gas collecting segment 12.
Second bleed section 21 and 11 equal length of the first bleed section and coaxial line, ensure that overall structure is identical, to air
Circulation effect it is good, the axial length of the second gas collecting segment 22 is greater than the axial length of the first gas collecting segment 12, ensure that cold airflow
Maximum capture range and ejector pipe 1 effective built-in length.
As optional embodiment, injection section 23, the freedom of injection section 23 are extended in the free end of the second bleed section 21
The shape at end is adapted with rear body 6.
Specifically, the distance of the second bleed of free end distance section 21 of injection section 23 is not equal and close to 6 section of rear body
Length is greater than the length far from 6 section of rear body, and the length of ejector pipe 1 is depending on the length of 3 jet pipe 4 of engine, this reality
It applies distance of 1 free end of ejector pipe away from 4 free end of jet pipe in example and is greater than 150mm, 23 free end of injection section is free away from ejector pipe 1
End is less than 350mm.
As optional embodiment, the second gas collecting segment 22 offers at least two ventholes 24 close to 3 one end of engine.
The cold air for enabling air intake duct 5 to flow into is flowed out by venthole 24 along the direction that high-temperature fuel gas sprays, and heat dissipation is increased, and is reduced heat-insulated
Temperature between cover 2 and the fuselage of unmanned plane, avoids heat from assembling, wherein venthole 24 is at least 2.
As optional embodiment, ejector pipe 1 is fixedly connected with heat shield 2 by connector.Pass through connector fission
Formula, which is connected, can avoid replacement whole device, save the cost for the part of damage.
As optional embodiment, as shown in Fig. 3~Fig. 5, connector includes the first connector 7 and/or the second connection
Part 8, the first connector 7 are set to one end of 1 minor diameter of ejector pipe, and the second connector 8 is set to the one of 1 major diameter of ejector pipe
End.
Specifically, the first connector 7 is fixed on the free end of the first bleed section 11 and the smaller diameter end of the second bleed section 21
Between, the second connector 8 is fixed between the free end of the first gas collecting segment 12 and the second gas collecting segment 22, the first connector 7 and
Two connectors 8 can be identical connector, can also be different connectors, and preferably each bearing's connector number is four and week
To being uniformly distributed, two positions ensure that the reliability that ejector pipe 1 and heat shield 2 are fixed end to end.
Preferably, the first connector 7 is U-shaped part, and the second connector 8 is Z-type part, the first connector 7 and the second connector 8
It can be screwed, since the joint face gradient of ejector pipe 1 and heat shield 2 is small at the first connector 7, with U-shaped part support effect
Good, the joint face gradient of 8 ejector pipe 1 of the second connector and heat shield 2 is big and is located at cold airflow arrival end, and the fixation of Z-type part is more firm
Gu.
Above description is only a specific implementation of the present invention, but the protection scope of the utility model is not limited to
In this, anyone skilled in the art within the technical scope disclosed by the utility model, can readily occur in variation
Or replacement, it should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with the power
Subject to the protection scope that benefit requires.
Claims (10)
1. a kind of bleed radiator, which is characterized in that including ejector pipe and heat shield, the heat shield is fixed on rear body
Interior, the ejector pipe is fixed in the heat shield and is equipped with gap between the side wall of the two to form drainage channel, unmanned plane
Air intake duct communicated with the air inlet of engine and the part cold airflow of air intake duct outflow is by generating after the engine
Combustion gas, the jet pipe of the engine is connected with the ejector pipe and the combustion gas that sprays through the jet pipe is through the ejector pipe
Outside injection to engine nacelle, the part cold airflow of the air intake duct outflow can flow into the drainage channel and the ejector pipe
It is interior that cooling is thermally shielded with the combustion gas sprayed to the jet pipe.
2. a kind of bleed radiator according to claim 1, which is characterized in that the ejector pipe includes the first bleed section
With the first gas collecting segment, first gas collecting segment and the end to end formation trumpet type of the first bleed section and first gas collecting segment
Free end diameter be greater than the first bleed section free end diameter.
3. a kind of bleed radiator according to claim 2, which is characterized in that the heat shield includes the second gas collecting segment
With the second bleed section, second gas collecting segment and the end to end formation trumpet type of the second bleed section and the heat shield and institute
It is identical to state ejector pipe axis.
4. a kind of bleed radiator according to claim 3, which is characterized in that the second bleed section and described first
Bleed segment length is equal, and the axial length of second gas collecting segment is greater than the axial length of first gas collecting segment.
5. a kind of bleed radiator according to claim 3, which is characterized in that prolong the free end of the second bleed section
Injection section is stretched out, the shape of the free end of the injection section is adapted with the rear body.
6. a kind of bleed radiator according to claim 3, which is characterized in that second gas collecting segment is close to the hair
Motivation one end offers at least two ventholes.
7. a kind of bleed radiator according to claim 1, which is characterized in that the ejector pipe and the heat shield are logical
Connector is crossed to be fixedly connected.
8. a kind of bleed radiator according to claim 7, which is characterized in that the connector includes the first connector
And/or second connector, first connector are set to one end of the ejector pipe minor diameter, the second connector setting
In one end of the ejector pipe major diameter.
9. a kind of bleed radiator according to claim 8, which is characterized in that first connector is U-shaped part, institute
Stating the second connector is Z-type part.
10. a kind of bleed radiator according to claim 1, which is characterized in that the ejector pipe and the heat shield
The distance between be 15mm~30mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821958553.8U CN209410346U (en) | 2018-11-26 | 2018-11-26 | Bleed radiator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821958553.8U CN209410346U (en) | 2018-11-26 | 2018-11-26 | Bleed radiator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209410346U true CN209410346U (en) | 2019-09-20 |
Family
ID=67935327
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821958553.8U Active CN209410346U (en) | 2018-11-26 | 2018-11-26 | Bleed radiator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209410346U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173137A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Cooling air inlet channel of helicopter |
| CN112412656A (en) * | 2020-11-13 | 2021-02-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Full-composite-material skin aircraft engine cabin cooling structure |
| CN112648109A (en) * | 2020-12-28 | 2021-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Airframe external air entraining device based on cooling of jet pipe of hypersonic aircraft |
| CN113044228A (en) * | 2019-12-27 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Installation method of airplane equipment |
-
2018
- 2018-11-26 CN CN201821958553.8U patent/CN209410346U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113044228A (en) * | 2019-12-27 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Installation method of airplane equipment |
| CN112173137A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Cooling air inlet channel of helicopter |
| CN112412656A (en) * | 2020-11-13 | 2021-02-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Full-composite-material skin aircraft engine cabin cooling structure |
| CN112648109A (en) * | 2020-12-28 | 2021-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Airframe external air entraining device based on cooling of jet pipe of hypersonic aircraft |
| CN112648109B (en) * | 2020-12-28 | 2022-07-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Airframe external air entraining device based on hypersonic aircraft spray pipe cooling |
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