CN114320658A - Thrust vector nozzle applied to small turbojet engine and design method thereof - Google Patents
Thrust vector nozzle applied to small turbojet engine and design method thereof Download PDFInfo
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- CN114320658A CN114320658A CN202210057463.6A CN202210057463A CN114320658A CN 114320658 A CN114320658 A CN 114320658A CN 202210057463 A CN202210057463 A CN 202210057463A CN 114320658 A CN114320658 A CN 114320658A
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 239000011248 coating agent Substances 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims abstract description 5
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 claims description 10
- 239000007787 solid Substances 0.000 claims description 5
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical group [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 6
- 239000010410 layer Substances 0.000 description 27
- 239000000463 material Substances 0.000 description 4
- 239000002356 single layer Substances 0.000 description 3
- 238000005253 cladding Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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Abstract
The invention discloses a thrust vector nozzle applied to a small turbojet engine and a design method thereof. The thrust vector nozzle is used for changing the direction of jet air flow and further changing the direction of thrust to control the flight posture of the unmanned aerial vehicle, and comprises an inner nozzle, an outer fixed layer and a jet flow vector device, wherein the outer fixed layer is arranged on the inner nozzle in a coating mode, and the jet flow vector device is welded and fixed at the end positions of the inner nozzle and the outer fixed layer. The clearance between the inner nozzle and the engine nozzle is 5 mm. And two groups of rudder angles are fixedly arranged on the jet flow vector device. The two groups of rudder angles respectively correspond to an X axis of the jet flow vector device and a Y axis of the jet flow vector device. The thrust vector nozzle is of a double-layer structure, has high strength, and has a gap with the nozzle of the engine, so that the efficiency of the engine is greatly improved, and the conversion rate of the thrust vector nozzle to the power of the engine is up to 93 percent.
Description
Technical Field
The invention relates to a vector nozzle for an engine, in particular to a thrust vector nozzle applied to a small turbojet engine, and also relates to a design method of the thrust vector nozzle.
Background
The vector nozzle changes the direction of the jet air flow and further changes the vector by controlling the deflection of the nozzle of the propeller, and changes part of the thrust direction through the deflection of the nozzle, thereby controlling the posture of the aircraft and leading the facing angle of the aircraft to be different from the advancing direction.
Fixed wing unmanned aerial vehicle has the range far away for many rotor unmanned aerial vehicle, characteristics such as fast and the altitude of flight height of voyage, the engine of current fixed wing unmanned aerial vehicle majority is the ducted fan, partly be the turbojet engine in addition, to the engine of this kind of jet-propelled power supply, the use of vector spout can greatly improve fixed wing unmanned aerial vehicle mobility undoubtedly, however, the vector spout is not good to the conversion rate of engine power down, unmanned aerial vehicle's mobility has been influenced.
Disclosure of Invention
Based on this, it is necessary to provide a thrust vector nozzle applied to a small turbojet engine and a design method thereof, aiming at the problem that the conversion rate of the current vector nozzle to the engine power is poor and the maneuverability of the unmanned aerial vehicle is affected.
A thrust vector nozzle for a small turbojet engine, comprising:
an inner spout;
the outer fixed layer is coated on the inner nozzle; and
the jet flow vector device is welded and fixed at the end positions of the inner nozzle and the outer fixing layer; and two groups of rudder angles are fixedly arranged on the jet flow vector device.
The thrust vector nozzle is of a double-layer structure, has high strength, and has a gap with a nozzle of the engine, so that the efficiency of the engine is greatly improved, and the conversion rate of the thrust vector nozzle to the power of the engine is up to 93 percent.
In one embodiment, the inner spout is in a conical structure; the clearance between the inner nozzle and the engine nozzle is 5 mm.
In one embodiment, the inner spout and the outer fixed layer are combined into a double-layer structure.
Furthermore, twenty groups of patches are arranged between the inner nozzle and the outer fixing layer, and the inner nozzle is welded and fixed with the outer fixing layer through the patches.
Still further, the inner nozzle and the outer solid layer are made of 304 steel materials with the thickness of 0.5 mm.
In one embodiment, six groups of long patches are fixedly arranged at the position of the outer fixing layer, which faces away from the jet flow vector device; six groups of the long patches are uniformly arranged on the outer part of the inner spout in a surrounding way.
Furthermore, an aluminum ring is fixedly connected between the six groups of long patches and is fixed on the turbojet engine.
In one embodiment, the two sets of rudder angles respectively correspond to an X axis of the jet flow vector device and a Y axis of the jet flow vector device; the rudder angle is used for controlling the rotation angle of the jet flow vector device.
A design method comprising the steps of:
s1, designing the inner nozzle into a conical structure, and manufacturing the inner nozzle by adopting 0.5mm 304 steel;
s2, coating and fixing an outer fixing layer on the outer part of the inner nozzle, and controlling a gap of 5mm between the inner nozzle and the engine nozzle;
s3 fixing the jet stream vector device at the end of the inner jet orifice and the outer fixed layer.
Above-mentioned design method, based on the tapered design for the main part of thrust vector spout is the tapered structure, thereby more excellent improvement engine efficiency, through the outside cladding external fixation layer of interior spout, obtains the thrust vector spout that is bilayer structure, and compared with single-layer construction, intensity is higher, and stability is better, and, leave 5 mm's clearance between control interior spout and the engine spout, improve the efficiency of engine, in addition, adopt light material preparation (0.5 mm's 304 steel), weight reduction.
In one embodiment, the design method is used for designing and obtaining the thrust vector nozzle applied to the small turbojet engine.
Compared with the prior art, the invention has the beneficial effects that:
the thrust vector nozzle is of a double-layer structure, has high strength, and has a 5mm gap with the nozzle of the engine, so that the efficiency of the engine is greatly improved, and tests prove that the thrust vector nozzle has the conversion rate of engine power up to 93%.
The design method is based on the conical design, the main body part of the thrust vector nozzle is in the conical structure, so that the engine efficiency is improved better, the thrust vector nozzle in the double-layer structure is obtained by coating the outer fixed layer on the outer part of the inner nozzle, compared with the thrust vector nozzle in the single-layer structure, the thrust vector nozzle is higher in strength and better in stability, a gap of 5mm is reserved between the inner nozzle and the engine nozzle, the efficiency of the engine is improved, and in addition, the thrust vector nozzle is made of light materials (304 steel of 0.5 mm), so that the weight is reduced.
Drawings
Fig. 1 is a schematic structural diagram of a thrust vector nozzle applied to a small turbojet engine according to embodiment 1 of the present invention.
Fig. 2 shows a top view of fig. 1.
Description of the main elements
1. An inner spout; 2. an outer fixing layer; 3. a jet flow vector device; 4. and (4) rudder angle.
The present invention is described in further detail with reference to the drawings and the detailed description.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
Example 1
Referring to fig. 1-2, the present embodiment provides a thrust vector nozzle applied to a small turbojet engine, which is used for changing the direction of the jet air flow, so as to change the thrust direction to control the flight attitude of the unmanned aerial vehicle. The thrust vector nozzle comprises an inner nozzle 1, an outer fixed layer 2 coated on the inner nozzle 1 and a jet flow vector device 3.
The inner nozzle 1 is in a conical structure, and can improve the efficiency of the engine better. The gap between the inner nozzle 1 and the engine nozzle is 5 mm. Twenty groups of patches are arranged between the inner nozzle 1 and the outer fixed layer 2, and the inner nozzle 1 is welded and fixed with the outer fixed layer 2 through the patches. The inner nozzle 1 and the outer fixing layer 2 form a double-layer structure so as to ensure the strength of the thrust vector nozzle. Interior spout 1 and solid layer 2 all adopt 0.5 mm's 304 steel, reduce unmanned aerial vehicle's weight based on 304 steel.
Six groups of long patches are fixedly arranged at the position of the outer fixed layer 2, which is back to the jet flow vector device 3. Six groups of long patches are uniformly arranged around the outer part of the inner spout 1. And an aluminum ring is fixedly connected between the six groups of long patches and is fixed on the turbojet engine. The frame structure formed by the long patches and the aluminum ring realizes the tight connection between the nozzle of the engine and the thrust vector nozzle.
The jet flow vector device 3 is welded and fixed at the end positions of the inner nozzle 1 and the outer fixing layer 2. Two groups of rudder angles 4 are fixedly arranged on the jet flow vector device 3. The two steering angles 4 correspond to the X-axis of the jet flow vector device 3 and the Y-axis of the jet flow vector device 3, respectively. The steering angle 4 is used to control the rotation angle of the jet flow vector device 3. Based on X axle and Y axle, jet flow vector device 3 can carry out 360 rotations to promote unmanned aerial vehicle.
In summary, the thrust vector nozzle of the present embodiment has the following advantages compared to the current vector nozzle: the thrust vector nozzle of this embodiment is bilayer structure, and intensity is higher, has 5 mm's clearance between the nozzle with the engine is from to greatly improve engine efficiency, and, through experimental proof, the thrust vector nozzle of this embodiment, to engine power's conversion rate reach 93%.
Example 2
This embodiment provides a design method for designing a thrust vector nozzle for a small turbojet engine as described in embodiment 1. The design method comprises the following steps:
s1, designing the inner spout 1 into a conical structure, and manufacturing the inner spout 1 by adopting 0.5mm 304 steel;
s2, coating and fixing an outer fixing layer 2 outside the inner nozzle 1, and controlling a gap of 5mm between the inner nozzle 1 and an engine nozzle;
s3 fixing the jet stream vector unit 3 at the end of the inner spout 1 and the outer fixed layer 2.
To sum up, the design method of this embodiment is based on the design of the tapered for the main part of thrust vector spout is the tapered structure, thereby better improvement engine efficiency, through the outside cladding solid layer 2 of spout 1 in, obtain the thrust vector spout that is bilayer structure, compare in single layer construction, intensity is higher, stability is better, and, leave 5 mm's clearance between spout 1 and the engine spout in the control, improve the efficiency of engine, in addition, adopt light material preparation (0.5 mm's 304 steel), weight reduction.
For the naming of each component referred to, the function described in the specification is used as the standard for naming, but is not limited by the specific term used in the present invention, and those skilled in the art can also select other terms to describe each component name of the present invention.
Claims (10)
1. A thrust vector nozzle for a small turbojet engine, comprising:
an inner spout (1);
an outer fixed layer (2) coated on the inner spout (1); and
a jet flow vector device (3) welded and fixed at the end positions of the inner nozzle (1) and the outer fixing layer (2); and two groups of rudder angles (4) are fixedly arranged on the jet flow vector device (3).
2. The thrust vector nozzle applied to the small turbojet engine as recited in claim 1, characterized in that the inner nozzle (1) is of a cone-shaped structure;
the clearance between the inner nozzle (1) and the engine nozzle is 5 mm.
3. The thrust vector nozzle applied to the small turbojet engine as recited in claim 1, wherein the inner nozzle (1) and the outer solid layer (2) are combined into a double-layer structure.
4. The thrust vector nozzle applied to the small turbojet engine as recited in claim 3, wherein twenty sets of patches are arranged between the inner nozzle (1) and the outer fixed layer (2), and the inner nozzle (1) is welded and fixed with the outer fixed layer (2) through the patches.
5. The thrust vector nozzle applied to the small turbojet engine as recited in claim 4, wherein the inner nozzle (1) and the outer solid layer (2) are made of 0.5mm 304 steel.
6. The thrust vector nozzle applied to the small turbojet engine as recited in claim 1, characterized in that six groups of long patches are fixedly arranged at the position of the outer fixed layer (2) facing away from the jet flow vector device (3);
six groups of the long patches are uniformly arranged around the outer part of the inner spout (1).
7. The thrust vector nozzle applied to the small turbojet engine as recited in claim 6, wherein an aluminum ring is fixedly connected between the six sets of long patches and is fixed on the turbojet engine.
8. The thrust vectoring nozzle for a small turbojet engine according to claim 1, characterized in that the two sets of rudder angles (4) correspond respectively to the X axis of the jet vectoring device (3) and to the Y axis of the jet vectoring device (3);
the rudder angle (4) is used for controlling the rotation angle of the jet flow vector device (3).
9. A design method, comprising the steps of:
s1, designing the inner nozzle into a conical structure, and manufacturing the inner nozzle by adopting 0.5mm 304 steel;
s2, coating and fixing an outer fixing layer on the outer part of the inner nozzle, and controlling a gap of 5mm between the inner nozzle and the engine nozzle;
s3 fixing the jet stream vector device at the end of the inner jet orifice and the outer fixed layer.
10. A design method according to claim 9, wherein the design method is used for designing a thrust vector nozzle for a small turbojet engine according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210057463.6A CN114320658A (en) | 2022-01-19 | 2022-01-19 | Thrust vector nozzle applied to small turbojet engine and design method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210057463.6A CN114320658A (en) | 2022-01-19 | 2022-01-19 | Thrust vector nozzle applied to small turbojet engine and design method thereof |
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| CN114320658A true CN114320658A (en) | 2022-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210057463.6A Pending CN114320658A (en) | 2022-01-19 | 2022-01-19 | Thrust vector nozzle applied to small turbojet engine and design method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114856857A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Integrated type round-square casing with multiple channels |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4809932A (en) * | 1986-12-20 | 1989-03-07 | Messerschmitt-Bokow-Blohm GmbH | Thrust vector control for aircraft |
| CN205872443U (en) * | 2016-05-10 | 2017-01-11 | 成都前沿动力科技有限公司 | Rotary mechanism suitable for VTOL unmanned aerial vehicle 90 degree thrust vectoring nozzle |
| CN106968831A (en) * | 2016-01-14 | 2017-07-21 | 王佐良 | A kind of rudder formula vector engine |
| CN110513216A (en) * | 2019-09-10 | 2019-11-29 | 西北工业大学 | A kind of mechanical vector spray of bellows structure |
| CN113277079A (en) * | 2021-05-12 | 2021-08-20 | 上海工程技术大学 | Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control |
-
2022
- 2022-01-19 CN CN202210057463.6A patent/CN114320658A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4809932A (en) * | 1986-12-20 | 1989-03-07 | Messerschmitt-Bokow-Blohm GmbH | Thrust vector control for aircraft |
| CN106968831A (en) * | 2016-01-14 | 2017-07-21 | 王佐良 | A kind of rudder formula vector engine |
| CN205872443U (en) * | 2016-05-10 | 2017-01-11 | 成都前沿动力科技有限公司 | Rotary mechanism suitable for VTOL unmanned aerial vehicle 90 degree thrust vectoring nozzle |
| CN110513216A (en) * | 2019-09-10 | 2019-11-29 | 西北工业大学 | A kind of mechanical vector spray of bellows structure |
| CN113277079A (en) * | 2021-05-12 | 2021-08-20 | 上海工程技术大学 | Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114856857A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Integrated type round-square casing with multiple channels |
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Application publication date: 20220412 |
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