CN109502034B - Small-bore aircraft gas rudder keeps off fire structure - Google Patents
Small-bore aircraft gas rudder keeps off fire structure Download PDFInfo
- Publication number
- CN109502034B CN109502034B CN201811509440.4A CN201811509440A CN109502034B CN 109502034 B CN109502034 B CN 109502034B CN 201811509440 A CN201811509440 A CN 201811509440A CN 109502034 B CN109502034 B CN 109502034B
- Authority
- CN
- China
- Prior art keywords
- rudder
- gas
- gas rudder
- fire
- small
- 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
- 230000000903 blocking effect Effects 0.000 claims abstract description 23
- 239000000463 material Substances 0.000 claims description 4
- 239000003870 refractory metal Substances 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 3
- WUUZKBJEUBFVMV-UHFFFAOYSA-N copper molybdenum Chemical group [Cu].[Mo] WUUZKBJEUBFVMV-UHFFFAOYSA-N 0.000 claims description 2
- 230000002093 peripheral effect Effects 0.000 abstract description 6
- 230000008595 infiltration Effects 0.000 description 3
- 238000001764 infiltration Methods 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- SBYXRAKIOMOBFF-UHFFFAOYSA-N copper tungsten Chemical compound [Cu].[W] SBYXRAKIOMOBFF-UHFFFAOYSA-N 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Tires In General (AREA)
Abstract
The invention provides a small-caliber aircraft gas rudder fire blocking structure, which belongs to the technical field of aircraft gas rudders and comprises a gas rudder support, a gas rudder shaft, a gas rudder sheet and a fire blocking cover, wherein the gas rudder support is of an integral structure, the gas rudder shaft in four directions is arranged, the gas rudder shaft is a rotating shaft of the gas rudder sheet, the gas rudder sheet extends into tail flames of an aircraft engine, and the fire blocking cover is of an integral ring structure and is arranged at an outlet of a jet pipe of the aircraft engine to protect the gas rudder shaft and a peripheral structure and prevent the tail flames of the engine from being ablated. The small-caliber aircraft gas rudder fire blocking structure can effectively protect tail flames of an aircraft engine, prevent the tail flames from damaging a gas rudder shaft and a peripheral structure, and simultaneously ensure that the gas rudder shaft freely rotates.
Description
Technical Field
The invention belongs to the technical field of aircraft gas rudders, and relates to a gas rudder fire blocking structure, in particular to a thermal fire prevention structure of a gas rudder shaft of a small-caliber aircraft.
Background
The gas rudder is arranged at the rear end of a nozzle of an aircraft engine, provides control force by using tail flame of the engine, and is an important part for stable flight and quick maneuvering of the small-caliber aircraft. However, the temperature of the tail flame of the aircraft engine is more than 2000 ℃, the flow rate of the nozzle is high, the ejected gas is mixed with solid particles, the erosion and ablation on the gas rudder shaft and the surrounding structure are serious, the rotation of the gas rudder shaft can be blocked due to the accumulation of high temperature and solid particles, and the fireproof structure of the gas rudder is a difficult point for designing the gas rudder of the aircraft. The traditional large-caliber aircraft adopts a large amount of refractory metal tungsten copper infiltration, graphite and a complex structure during design due to relative allowance of space weight, and is hard to resist ablation and thermal environment influence. However, the small-caliber aircraft is light in weight and small in space, the requirement on the design of a fire-proof structure of the gas vane is higher, the fire-proof design of the gas vane of only a few types of small-caliber aircraft in China does not break through the limitation, and the refractory metal tungsten copper-infiltrated integral design is still adopted.
Disclosure of Invention
Aiming at the defects or improvement requirements in the prior art, the invention provides a fire blocking structure of a small-caliber aircraft gas rudder, which adopts a split design, uses metal with lower density and a flange flanging fire blocking structure, realizes thermal protection on a gas rudder shaft and a peripheral structure, and has the advantages of simple and reliable structure and light weight.
In order to achieve the purpose, the invention provides a fire blocking structure of a gas rudder of a small-caliber aircraft, which comprises a gas rudder bracket, a gas rudder shaft, a gas rudder sheet and a fire blocking cover.
Specifically, the gas rudder support is of an integral structure and can be provided with gas rudder shafts in four directions.
The outer circle of the gas rudder shaft is provided with a flange flanging, and a groove is formed in the flange flanging.
And the gas rudder piece is provided with a boss matched with the groove at the flange flanging position on the excircle of the gas rudder shaft.
The fire blocking cover is of a whole ring structure and is arranged on the gas rudder support; the inner surface of the fire shield is a conical surface consistent with the expansion angle of an engine spray pipe, an engine nozzle is wrapped, and a semicircular groove corresponding to the gas rudder shaft is formed in the fire shield.
Further, the gas rudder support is integrally machined and formed, two round holes for mounting the bearings are formed in each position, the gas rudder shaft is supported, all round holes are integrally machined at one time, and coaxiality and verticality are guaranteed.
Furthermore, the semicircular groove is formed in the fire shield corresponding to the flange flanging on the gas rudder shaft, the flange flanging is just positioned in the semicircular groove after assembly, gaps between the flange flanging and the semicircular groove in three directions are uniform, namely a concave gap cavity is formed between the gas rudder shaft and the fire shield, the concave cavity not only ensures that the gas rudder shaft can normally rotate, but also prevents tail flame airflow of an engine from directly flowing to the periphery of the fire shield, and after the tail flame airflow is blocked by the concave cavity, the speed of the tail flame airflow of the engine is reduced, the temperature is reduced, and the damage to the gas rudder shaft and the peripheral structure is weakened.
In general, the above technical solutions contemplated by the present invention can achieve the following beneficial effects:
through the optimized design, the invention provides the small-caliber aircraft gas rudder fire blocking structure, which adopts the split design, uses metal with lower density and a flange flanging fire blocking structure, realizes the thermal protection on a gas rudder shaft and a peripheral structure, and has simple and reliable structure and light weight.
Drawings
FIG. 1 is a schematic view of a small-caliber aircraft gas rudder fire-blocking structure according to an embodiment of the invention;
fig. 2 is a schematic cross-sectional view of an aircraft rudder firestopping structure in an embodiment of the invention.
In the drawings, like reference numerals are used to designate like elements or structures, wherein:
the gas rudder comprises a gas rudder support 1, a gas rudder shaft 2, a gas rudder sheet 3, a fire blocking cover 4, a flange flanging 5, a groove 6, a boss 7 and a semicircular groove 8.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Fig. 1 is a schematic view of a fire blocking structure of a small-caliber aircraft gas rudder in an embodiment of the present invention, and fig. 2 is a schematic cross-sectional view of the fire blocking structure of the aircraft gas rudder in an embodiment of the present invention.
In order to achieve the purpose, the invention provides a fire blocking structure of a gas rudder of a small-caliber aircraft, which comprises a gas rudder bracket, a gas rudder shaft, a gas rudder sheet and a fire blocking cover.
Specifically, gas rudder support 1 is overall structure, all is provided with the round hole of installation gas rudder axle 2 bearing in four directions, and every direction respectively has two round holes of settling the bearing, settles gas rudder axle 2 in the bearing, realizes the support to gas rudder axle 2, guarantees that gas rudder axle 2 can the free rotation.
The gas rudder shaft 2 is made of molybdenum-copper-infiltrated material, a flange flanging 5 is arranged on the outer circle of the gas rudder shaft, and a groove 6 matched with the gas rudder piece 3 is arranged at the flange flanging 5.
The gas rudder piece 3 is made of tungsten copper infiltration refractory metal, a boss 7 is arranged on the gas rudder piece 3, and the boss 7 is arranged in a groove 6 of the gas rudder shaft 2.
The fire blocking cover 4 is of a molybdenum copper infiltration material whole ring structure, is installed on the gas rudder support 1 through screws, is a conical surface consistent with the expansion angle of an engine spray pipe in shape, wraps an engine nozzle, and is provided with a semicircular groove 8 corresponding to the excircle of the gas rudder shaft 2.
The flange flanging 5 on the gas rudder shaft 2 corresponds to the semicircular groove 8 on the fire shield 4, the flange flanging 5 is just positioned in the semicircular groove 8 on the fire shield 4 after assembly, and uniform gaps are ensured between the flange flanging 6 and the semicircular groove 8 in three directions; the gap can be 0.5-3 mm.
In general, the above technical solutions contemplated by the present invention can achieve the following beneficial effects:
through the optimized design, the small-caliber aircraft gas rudder fire blocking structure provided by the invention adopts a split design, uses metal with lower density and a flange flanging fire blocking structure, realizes thermal protection on a gas rudder shaft and a peripheral structure, and has the advantages of simple and reliable structure and light weight.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. A small-caliber aircraft gas rudder fire blocking structure is characterized by comprising a gas rudder support, a gas rudder shaft, a gas rudder sheet and a fire blocking cover, wherein the gas rudder support is of an integral structure and is provided with the gas rudder shaft in four directions; the outer circle of the gas rudder shaft is provided with a flange flanging, and a groove is formed in the flange flanging; the gas rudder piece is provided with a boss matched with a groove at the flange flanging position on the excircle of the gas rudder shaft; the groove at the flange flanging position of the gas rudder shaft is matched with the boss of the gas rudder sheet; the fire blocking cover is of a whole ring structure and is arranged on the gas rudder support; the inner surface of the fire shield is a conical surface consistent with the expansion angle of an engine spray pipe, an engine nozzle is wrapped, and a semicircular groove corresponding to a gas rudder shaft is formed in the fire shield; the gaps between the flange flanging and the semicircular groove in three directions are uniform.
2. The small-caliber aircraft rudder fire stopping structure as claimed in claim 1, wherein the rudder support is integrally formed, two circular holes for mounting bearings are formed in four directions, and the coaxiality and the verticality of the four-direction rudder shafts are ensured.
3. The small-caliber aircraft rudder fire stopping structure as claimed in claim 1, wherein each rudder shaft is provided with a flange, the corresponding fire stopping cover is provided with a semicircular groove, and the flange is just positioned in the semicircular groove after assembly.
4. The small-caliber aircraft rudder fire stopping structure as claimed in claim 1, 2 or 3, wherein gaps between the flange flanging and the semicircular groove in three directions are all 0.5-3 mm, and a concave gap cavity is formed between the rudder shaft and the fire stopping cover.
5. The small-caliber aircraft rudder fire stopping structure as claimed in claim 1, wherein the rudder shaft is made of a molybdenum-copper-infiltrated material.
6. The small-caliber aircraft rudder fire stopping structure as claimed in claim 1, wherein the rudder piece is made of tungsten-infiltrated refractory metal.
7. The small-caliber aircraft rudder fire stop structure as claimed in claim 1, wherein the fire stop cover is a molybdenum-copper infiltrated material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811509440.4A CN109502034B (en) | 2018-12-11 | 2018-12-11 | Small-bore aircraft gas rudder keeps off fire structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811509440.4A CN109502034B (en) | 2018-12-11 | 2018-12-11 | Small-bore aircraft gas rudder keeps off fire structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109502034A CN109502034A (en) | 2019-03-22 |
| CN109502034B true CN109502034B (en) | 2021-10-19 |
Family
ID=65752035
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811509440.4A Active CN109502034B (en) | 2018-12-11 | 2018-12-11 | Small-bore aircraft gas rudder keeps off fire structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109502034B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116538871B (en) * | 2023-07-05 | 2023-10-20 | 北京凌空天行科技有限责任公司 | Novel gas rudder and verification method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB8822798D0 (en) * | 1988-09-28 | 1988-11-02 | Short Brothers Ltd | Ducted fan turbine engine |
| FR2710951B1 (en) * | 1993-10-06 | 1995-11-03 | Snecma | Axisymmetric, convergent-divergent turbojet exhaust nozzle with reverse thrust. |
| RU2477446C1 (en) * | 2012-02-06 | 2013-03-10 | Марина Леонардовна Нефедова | Antiaircraft missile |
| CN107416213B (en) * | 2017-05-16 | 2020-03-24 | 上海航天控制技术研究所 | Take aircraft tail end fire resistive construction of gas vane |
| CN108007280B (en) * | 2017-12-28 | 2023-08-15 | 北京威标至远科技发展有限公司 | Steering engine heat-proof structure |
-
2018
- 2018-12-11 CN CN201811509440.4A patent/CN109502034B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109502034A (en) | 2019-03-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109502034B (en) | Small-bore aircraft gas rudder keeps off fire structure | |
| US6887035B2 (en) | Tribologically improved design for variable stator vanes | |
| US3779006A (en) | Flame shield for a gas turbine engine | |
| US20090110546A1 (en) | Feather Seals and Gas Turbine Engine Systems Involving Such Seals | |
| CN1982675A (en) | Variable stator vane assembly and bushing thereof | |
| CN107416213B (en) | Take aircraft tail end fire resistive construction of gas vane | |
| JP2003193806A (en) | Nozzle blade band for gas turbine engine | |
| KR970005490B1 (en) | Nozzle seal assembly with removable baseplate | |
| US10393010B2 (en) | Multi-arc bearing and turbocharger | |
| US11333358B2 (en) | One-piece combustion chamber | |
| US9845524B2 (en) | Fixture for application of coatings and method of using same | |
| US10890109B2 (en) | Turbocharger | |
| JP5524211B2 (en) | Titanium-resistant fire compressor casing, high-pressure compressor containing such casing, and aircraft engine with such compressor | |
| EP2835544B1 (en) | Bearing cage deflector | |
| JP6505061B2 (en) | Aircraft engine spinner with improved crosswind performance | |
| JP2017150798A (en) | Combustor assembly | |
| JP2022531385A (en) | Turbine ring assembly mounted on spacers | |
| CN106481482A (en) | A kind of miniature liquid electromotor solar heat protection flow-guiding structure | |
| EP2372212B1 (en) | Radial and axial compliant sliding seal incorporating spring capturing features for improved bearing plane sealing in an articulating nozzle | |
| KR940007338A (en) | Heavy oil powered turbocharger | |
| EP3715651B1 (en) | Bearing housing | |
| CN104074795A (en) | High-speed shaft seal structure | |
| JP2017081542A (en) | Method and system for cross engine debris avoidance | |
| CN112922681A (en) | Aeroengine rim sealing structure | |
| US3290887A (en) | Swivelable nozzle for a jet 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 |