CN111336014B - Aviation gas turbine - Google Patents
Aviation gas turbine Download PDFInfo
- Publication number
- CN111336014B CN111336014B CN202010154274.1A CN202010154274A CN111336014B CN 111336014 B CN111336014 B CN 111336014B CN 202010154274 A CN202010154274 A CN 202010154274A CN 111336014 B CN111336014 B CN 111336014B
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- Prior art keywords
- gas turbine
- plate
- protection plate
- sliding
- containing groove
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- 230000007246 mechanism Effects 0.000 claims abstract description 56
- 238000001125 extrusion Methods 0.000 claims description 18
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims description 2
- 241001465754 Metazoa Species 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 81
- 238000009434 installation Methods 0.000 description 9
- 229910000831 Steel Inorganic materials 0.000 description 5
- 239000010959 steel Substances 0.000 description 5
- 241000938605 Crocodylia Species 0.000 description 3
- 241000238631 Hexapoda Species 0.000 description 3
- 238000003825 pressing Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
- F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to the field of turbines, in particular to an aviation gas turbine, which comprises a gas turbine body, a protection plate, a cushion protection mechanism, a fixing mechanism, an anti-skidding mechanism and a pushing mechanism, wherein an annular sliding cavity is formed in a shell, close to a fan, of the gas turbine body, the protection plate is used for being mounted on a shell, close to one end of the fan, of the gas turbine body, a sliding containing groove is formed in the protection plate, an opening is formed in the protection plate on one side of the sliding containing groove, the two fixing mechanisms with the same specification are symmetrically distributed in two side walls of the sliding containing groove, the fixing mechanism comprises an annular plate and springs, the annular plate is arranged in the sliding containing groove, and the outer ring wall of the annular plate is elastically connected with the inner wall of the sliding containing groove through a plurality of uniformly distributed springs. The invention provides an aviation gas turbine which has the advantage of preventing small animals or devices from entering the gas turbine to damage the gas turbine.
Description
Technical Field
The invention relates to the field of turbines, in particular to an aviation gas turbine.
Background
Gas turbines are used as engines for aircraft such as helicopters and jet aircraft. The aircraft gas turbine is configured by a compressor, a combustor, and a turbine, and air taken in from an air inlet is compressed by the compressor to become high-temperature and high-pressure compressed air, and the combustor supplies fuel to the compressed air to burn the compressed air, thereby driving the turbine with high-temperature and high-pressure combustion gas. In the case of a helicopter, the rotor is rotated by the driving force of the turbine, and in the case of a jet aircraft, the thrust is obtained from the energy of the exhaust gas.
In a turbine constituting an aircraft gas turbine in which a plurality of stationary blades and moving blades are alternately arranged in a casing and a compressor is driven by using gas to drive the moving blades, it is easy that some small animals or devices enter the gas turbine during production and transportation, which causes accidents during subsequent launching and use, and after the installation is completed, dust accumulation is easily generated at blades during long-term use of the aircraft. Therefore, there is a need to provide an aircraft gas turbine engine that solves the above-mentioned technical problems.
Disclosure of Invention
In response to the problems of the prior art, the present invention provides an aircraft gas turbine.
The technical scheme adopted by the invention for solving the technical problems is as follows: an aviation gas turbine comprises a gas turbine body, a protection plate, a cushion protection mechanism, a fixing mechanism, an anti-skidding mechanism and a pushing mechanism, wherein an annular skidding cavity is formed in a shell, close to a fan, of the gas turbine body; the protection plate is arranged on the shell, close to one end of the fan, of the gas turbine body, a sliding containing groove is formed in the protection plate, and an opening is formed in the protection plate on one side of the sliding containing groove; the cushion protection mechanism is arranged in a sliding containing groove formed in the protection plate; the two fixing mechanisms with the same specification are symmetrically distributed in two side walls in the sliding containing groove, each fixing mechanism comprises an annular plate and a spring, the annular plates are arranged in the sliding containing groove, and the outer ring wall of each annular plate is elastically connected with the inner wall of the sliding containing groove through a plurality of uniformly distributed springs; the two anti-skid mechanisms with the same specification are symmetrically distributed on two sides of the opening of the protection plate, and the pushing mechanism is arranged in the protection plate; the anti-skidding mechanism is characterized in that a steel wire rope is installed in the protection plate through a pulley, one end of the steel wire rope is connected with the extrusion plate of the anti-skidding mechanism, the other end of the steel wire rope is connected with a baffle, the baffle is installed outside the protection mechanism, and the cross section of the baffle is arc-shaped, and a circular truncated cone-shaped through hole is formed in the baffle.
Preferably, the cushion protection mechanism comprises an installation cavity and a rubber pad, the installation cavity is formed in the middle of the inner sliding containing groove in the protection plate, and the rubber pad is fixedly embedded in the installation cavity.
Preferably, the anti-skidding mechanism comprises an extrusion plate and a pressure spring, one end of the extrusion plate is rotatably connected with the inner wall of the opening of the protection plate through a rotating shaft, and the middle part of the outer side wall of the extrusion plate is elastically connected with the inner wall of the opening of the protection plate through the pressure spring.
Preferably, pushing mechanism includes the threaded rod, promotes arc board and turn-button, the threaded rod is inserted and is established in the screw through-hole that the guard plate was seted up, the one end of threaded rod extends to and slides and holds the inslot and install the promotion arc board of rotating the connection, and the other end fixed mounting of threaded rod has the turn-button, pushing mechanism sets up with the opening on the guard plate relatively, the stripper plate outer end among the anti-skidding mechanism is equipped with the transition cambered surface.
Compared with the related art, the aviation gas turbine provided by the invention has the following beneficial effects:
(1) according to the aviation gas turbine provided by the invention, the annular plate in the protection plate is used for clamping the bottom of the gas turbine body, and the spring connected with the annular plate is compressed, so that the annular plate is firmly embedded on the gas turbine body to protect the bottom of the gas turbine body, and the damage to the inside of the gas turbine body caused by the fact that some insects, reptiles or devices enter the gas turbine body along one end of a fan of the gas turbine body is avoided.
(2) According to the aviation gas turbine, when the protection plate clamps the bottom of the gas turbine body through the sliding containing groove, when the gas turbine body initially slides into the protection plate, the gas turbine body extrudes the two extrusion plates to enable the two extrusion plates on the protection plate to be opened and compress the compression spring, and after the gas turbine body completely slides into the sliding containing groove in the protection plate, the compression spring pushes the two extrusion plates away, so that the containing channel at the opening is reduced, and the protection plate is prevented from sliding along the outer side of the gas turbine body shell.
Drawings
FIG. 1 is a schematic block diagram of a preferred embodiment of an aircraft gas turbine engine provided in accordance with the present invention;
FIG. 2 is a schematic structural view of a backup protection mechanism shown in an aircraft gas turbine provided by the present invention;
FIG. 3 is a schematic view of the overall structure of the fender of the present invention;
FIG. 4 is a schematic view of the internal structure of the fender of the present invention.
Reference numbers in the figures: 1. the gas turbine comprises a gas turbine body, 2, an annular sliding cavity, 3, a protection plate, 4, a sliding containing groove, 5, a cushion protection mechanism, 51, a mounting cavity, 52, a rubber cushion, 6, a fixing mechanism, 61, an annular plate, 62, a spring, 7, an anti-skidding mechanism, 71, a squeezing plate, 72, a pressure spring, 8, a pushing mechanism, 81, a threaded rod, 82, a pushing arc plate, 83, a rotating button, 9, a steel wire rope, 9a, a baffle, 9a1 and a through hole.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
Referring to fig. 1-4, an aviation gas turbine includes a gas turbine body 1, a protection plate 3, a cushion protection mechanism 5, a fixing mechanism 6, an anti-slip mechanism 7 and a pushing mechanism 8, wherein an outer casing of the gas turbine body 1 close to a fan is provided with an annular slip cavity 2 for mounting the protection plate 3 on a casing of the gas turbine body 1 close to one end of the fan, the protection plate 3 is provided with a slip containing groove 4, the protection plate 3 on one side of the slip containing groove 4 is provided with an opening, two fixing mechanisms 6 with the same specification are symmetrically distributed in two side walls of the slip containing groove 4, the fixing mechanism 6 includes an annular plate 61 and springs 62, the annular plate 61 is arranged in the slip containing groove 4, and an outer ring wall of the annular plate 61 is elastically connected with an inner wall of the slip containing groove 4 through a plurality of uniformly distributed springs 62, wherein, the opening on pushing mechanism 8 and the guard plate 3 sets up relatively, and pushing mechanism 8 sets up in the guard plate 3, pushing mechanism 8 includes threaded rod 81, promotion arc board 82 and turn button 83, threaded rod 81 is inserted and is established in the screw through-hole that the guard plate 3 was seted up, one end of threaded rod 81 extends to in the slip appearance groove 4 and installs the promotion arc board 82 of rotating the connection, and the other end fixed mounting of threaded rod 81 has turn button 83, the inside of guard plate 3 is installed wire rope 9 through the pulley, and the one end of wire rope 9 is connected the stripper plate 71 of antiskid 7, and the other end of wire rope 9 is connected baffle 9a, and baffle 9a installs in the outside of cushion protection mechanism 5, and the cross-section is arc be equipped with round platform shape through-hole a1 on the baffle 9a, when using, when the aviation gas worm wheel is in the process of starting acceleration, the combustion can be accelerated, the tail part generates huge impact force, the baffle plate 9a is pushed to stretch outwards, the steel wire rope 9 is driven to pull a rope, so that the extrusion plate is driven to open, the sundries accumulated inside are discharged, when the gas turbine body 1 is assembled and needs to be transported, the opened end of the protection plate 3 slides along the side of the shell with the fan end arranged on the gas turbine body 1, the protection plate 3 is sleeved at the bottom of the gas turbine body 1, after the gas turbine body 1 slides into the sliding containing groove 4 arranged on the protection plate 3, the annular plate 61 in the protection plate 3 clamps the bottom of the gas turbine body 1, the spring 62 connected with the annular plate 61 is compressed, so that the annular plate 61 is firmly embedded on the gas turbine body 1 to protect the bottom of the gas turbine body 1, and insects and reptiles are prevented from entering the gas turbine body 1 along one end of the fan of the gas turbine body 1, and cause the inside damage of gas turbine body 1, and when need install gas turbine body 1 on the aeronautical instrument, thereby rotate knob 83 and drive threaded rod 81 and inwards slide along the screw through-hole, consequently promote arc board 82 and withstand gas turbine body 1 under the effect of threaded rod 81 to guard plate 3 has seted up annular sliding chamber 2 through sliding container 4 on along gas turbine body 1 and outwards slides, and until guard plate 3 slides away from gas turbine body 1.
Referring to fig. 2, the cushion protection mechanism 5 is disposed in the sliding accommodating groove 4 formed in the protection plate 3, the cushion protection mechanism 5 includes an installation cavity 51 and a rubber pad 52, the installation cavity 51 is disposed in the middle of the sliding accommodating groove 4 formed in the protection plate 3, the rubber pad 52 is fixedly embedded in the installation cavity 51, and after the fan is installed at the end of the gas turbine body 1 and embedded in the sliding accommodating groove 4 formed in the protection plate 3, the rubber pad 52 is fixedly embedded in the installation cavity 51 formed in the sliding accommodating groove 4, so that the rubber pad 52 effectively protects the bottom of the gas turbine body 1.
Referring to fig. 2, two anti-slip mechanisms 7 with the same specification are symmetrically distributed at two sides of the opening of the protection plate 3, the anti-skid mechanism 7 comprises an extrusion plate 71 and a pressure spring 72, one end of the extrusion plate 71 is rotatably connected with the inner wall of the opening of the protection plate 3 through a rotating shaft, the middle part of the outer side wall of the extrusion plate 71 is elastically connected with the inner wall of the opening of the protection plate 3 through a pressure spring 72, when the gas turbine body 1 initially slides into the shield plate 3 while the shield plate 3 is seized at the bottom of the gas turbine body 1 by the sliding pocket 4, the gas turbine body 1 presses the two pressing plates 71 so that the two pressing plates 71 on the shield plate 3 open and compress the compression springs 72, after the gas turbine body 1 has completely slid into the sliding pocket 4 in the protective plate 3, the compression spring 72 pushes the two pressure plates 71 apart, thereby reducing the volume at the opening and preventing the shroud plate 3 from sliding along the outside of the casing of the gas turbine body 1. Wherein, the outer end of the extrusion plate 71 in the anti-skid mechanism 7 is provided with a transition arc surface to prevent the gas turbine body 1 from sliding into the sliding containing groove 4 in the protection plate 3.
The working principle of the aviation gas turbine provided by the invention is as follows: when the gas turbine body 1 is assembled and needs to be transported, one end of the protection plate 3, which is provided with an opening, slides along the side edge of the shell, which is provided with one end of the fan, of the gas turbine body 1, the protection plate 3 is sleeved at the bottom of the gas turbine body 1, when the protection plate 3 blocks the bottom of the gas turbine body 1 through the sliding containing groove 4, when the gas turbine body 1 initially slides into the protection plate 3, the gas turbine body 1 extrudes the two extrusion plates 71 to open the two extrusion plates 71 on the protection plate 3 and compress the pressure spring 72, after the gas turbine body 1 completely slides into the sliding containing groove 4 in the protection plate 3, the pressure spring 72 pushes the two extrusion plates 71 open, so that the containing groove at the opening is reduced, the protection plate 3 is prevented from sliding along the shell of the gas turbine body 1, and after the gas turbine body 1 slides into the sliding containing groove 4 arranged on the protection plate 3, the annular plate 61 in the protection plate 3 is used for clamping the bottom of the gas turbine body 1, at the moment, the spring 62 connected with the annular plate 61 is compressed, so that the annular plate 61 is firmly embedded on the gas turbine body 1 to protect the bottom of the gas turbine body 1, and the phenomenon that some insects and reptiles enter the gas turbine body 1 along one end of a fan of the gas turbine body 1 to cause damage to the inside of the gas turbine body 1 is avoided, after one end of the gas turbine body 1 provided with the fan is embedded into a sliding containing groove 4 formed in the protection plate 3, because the rubber pad 52 is fixedly embedded on an installation cavity 51 formed in the sliding containing groove 4, the rubber pad 52 effectively protects the bottom of the gas turbine body 1, and when the gas turbine body 1 is required to be installed on an aeronautical instrument, the rotating knob 83 is rotated to drive the threaded rod 81 to slide inwards along a threaded through hole, therefore, the arc plates 82 are pushed to abut against the gas turbine body 1 under the action of the threaded rods 81, so that the protection plate 3 slides outwards along the annular sliding cavity 2 formed in the gas turbine body 1 through the sliding containing groove 4 until the protection plate 3 slides away from the gas turbine body 1.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and the embodiments and descriptions given above are only illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. The aviation gas turbine is characterized by comprising a gas turbine body (1), a protection plate (3), a cushion protection mechanism (5), a fixing mechanism (6), an anti-skidding mechanism (7) and a pushing mechanism (8), wherein an annular sliding cavity (2) is formed in a shell, close to a fan, of the gas turbine body (1) and used for mounting the protection plate (3) on a shell, close to one end of the fan, of the gas turbine body (1), a sliding containing groove (4) is formed in the protection plate (3), and an opening is formed in the protection plate (3) on one side of the sliding containing groove (4); the cushion protection mechanism (5) is arranged in a sliding containing groove (4) formed in the protection plate (3); the two fixing mechanisms (6) with the same specification are symmetrically distributed in two side walls in the sliding containing groove (4), each fixing mechanism (6) comprises an annular plate (61) and a spring (62), the annular plates (61) are arranged in the sliding containing groove (4), and the outer ring wall of each annular plate (61) is elastically connected with the inner wall of the corresponding sliding containing groove (4) through a plurality of uniformly distributed springs (62); the two anti-skid mechanisms (7) with the same specification are symmetrically distributed on two sides of the opening of the protection plate (3), and the pushing mechanism (8) is arranged in the protection plate (3); wire rope (9) are installed through the pulley in the inside of guard plate (3), just the one end of wire rope (9) is connected stripper plate (71) of anti-skidding mechanism (7), just baffle (9a) are connected to the other end of wire rope (9), just baffle (9a) are installed the outside of mechanism (5) is protected to the pad, and the cross-section is convex be equipped with round platform shape through-hole (9a1) on baffle (9 a).
2. The aircraft gas turbine according to claim 1, wherein the protection means (5) comprises a mounting cavity (51) and a rubber pad (52), the mounting cavity (51) is arranged in the middle of the inner sliding groove (4) of the protection plate (3), and the rubber pad (52) is fixedly embedded in the mounting cavity (51).
3. The aircraft gas turbine as claimed in claim 1, wherein the anti-skid mechanism (7) comprises an extrusion plate (71) and a compression spring (72), one end of the extrusion plate (71) is rotatably connected with the inner wall of the opening of the protection plate (3) through a rotating shaft, and the middle part of the outer side wall of the extrusion plate (71) is elastically connected with the inner wall of the opening of the protection plate (3) through the compression spring (72).
4. The aircraft gas turbine as claimed in claim 1, wherein the pushing mechanism (8) comprises a threaded rod (81), a pushing arc plate (82) and a rotating button (83), the threaded rod (81) is inserted into a threaded through hole formed in the protection plate (3), one end of the threaded rod (81) extends into the sliding accommodating groove (4) and is provided with the pushing arc plate (82) which is rotatably connected, and the other end of the threaded rod (81) is fixedly provided with the rotating button (83).
5. The aircraft gas turbine according to claim 4, characterized in that the pushing means (8) are arranged opposite to the opening in the protective plate (3), and the outer end of the pressure plate (71) in the anti-slip means (7) is provided with a transition arc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010154274.1A CN111336014B (en) | 2020-03-07 | 2020-03-07 | Aviation gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010154274.1A CN111336014B (en) | 2020-03-07 | 2020-03-07 | Aviation gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111336014A CN111336014A (en) | 2020-06-26 |
| CN111336014B true CN111336014B (en) | 2021-08-20 |
Family
ID=71179805
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010154274.1A Active CN111336014B (en) | 2020-03-07 | 2020-03-07 | Aviation gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111336014B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201802505U (en) * | 2010-05-05 | 2011-04-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Gas turbine with external ducted blanking cap |
| WO2012038317A1 (en) * | 2010-09-24 | 2012-03-29 | Aaf Ltd. | Filter assembly, and pre-filter device and pre-filter mounting plate therefor |
| CN106837604A (en) * | 2016-11-04 | 2017-06-13 | 上海新力动力设备研究所 | A kind of embedded dust and moisture structure of missile propulsive plant |
| CN107191291A (en) * | 2017-07-13 | 2017-09-22 | 西安航天动力研究所 | The dust guard and its installation method of a kind of engine |
| CN107740730A (en) * | 2017-09-15 | 2018-02-27 | 江西洪都航空工业集团有限责任公司 | Blanking cover before a kind of supersonic speed lower jaw air intake duct |
-
2020
- 2020-03-07 CN CN202010154274.1A patent/CN111336014B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201802505U (en) * | 2010-05-05 | 2011-04-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Gas turbine with external ducted blanking cap |
| WO2012038317A1 (en) * | 2010-09-24 | 2012-03-29 | Aaf Ltd. | Filter assembly, and pre-filter device and pre-filter mounting plate therefor |
| CN106837604A (en) * | 2016-11-04 | 2017-06-13 | 上海新力动力设备研究所 | A kind of embedded dust and moisture structure of missile propulsive plant |
| CN107191291A (en) * | 2017-07-13 | 2017-09-22 | 西安航天动力研究所 | The dust guard and its installation method of a kind of engine |
| CN107740730A (en) * | 2017-09-15 | 2018-02-27 | 江西洪都航空工业集团有限责任公司 | Blanking cover before a kind of supersonic speed lower jaw air intake duct |
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| Publication number | Publication date |
|---|---|
| CN111336014A (en) | 2020-06-26 |
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Effective date of registration: 20210721 Address after: 719000 shop on the second floor of building 3, Yuyang East Village resettlement community, Xiyi Road, Yuyang District, Yulin City, Shaanxi Province Applicant after: Shaanxi Blue Sky Aviation Club Co.,Ltd. Address before: 241000 Torch Industrial Park, torch Second Road, Yijiang District, Wuhu City, Anhui Province Applicant before: Yue Baoli |
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Effective date of registration: 20240423 Address after: 719000 Shop 1, Jinlin Community, Yima Road, Yuyang District, Yulin City, Shaanxi Province Patentee after: Yuhe Aircraft Manufacturing Co.,Ltd. in Yuyang District Yulin City Country or region after: China Address before: 719000 shop on the second floor of building 3, Yuyang East Village resettlement community, Xiyi Road, Yuyang District, Yulin City, Shaanxi Province Patentee before: Shaanxi Blue Sky Aviation Club Co.,Ltd. Country or region before: China |