CN108699969B - Dust-proof device of engine - Google Patents
Dust-proof device of engine Download PDFInfo
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- CN108699969B CN108699969B CN201680078646.9A CN201680078646A CN108699969B CN 108699969 B CN108699969 B CN 108699969B CN 201680078646 A CN201680078646 A CN 201680078646A CN 108699969 B CN108699969 B CN 108699969B
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- dust
- cyclone
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- 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
- F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cyclones (AREA)
Abstract
The invention is used to protect a gas turbine engine from dust and foreign matter. A dust-proof device for engine includes a cyclone, a cyclone panel fixed between the outside and the inside of the cyclone forming a dust-proof passage. In order to adapt the dust protection to engines with frontal air intake and to ensure ease of operation, a second configuration of dust protection for aircraft engines comprises a cyclone fixed between an outer and an inner cyclone panel, the cyclone panel forming an elongated housing along the engine axis with an inwardly disposed front cyclone panel. At the exit of the dust-proof device, a fairing is arranged in the shell. The hinge system has an external deployment with a structure that ensures the rotation of the dust guard housing. The arrangement of the cyclones and the cross-section of the dust-concentrating passage for extraction are related in a specified geometrical relationship.
Description
The present invention relates to the field of aeronautical engineering, in particular for protecting gas turbine engines from dust and foreign bodies. It can also be used in automobiles and industries to remove dust and foreign matter from the air.
by technical nature and effect, the most similar machine to the claimed solution is the multiple cyclone dust guard of VNIITRANSMASH JSC (patents RU 2181439, IPC F02C7/052 published on 4/20/2002), which consists of a straight cyclone fixed on an outer pipe and an inner pipe plate, which cyclone forms a dust collector cavity with a dust removal passage.
The dust-proof device has the following defects:
The cleanliness is low, and the size and weight of the whole dust-proof device are large;
Lack of operational convenience (in particular ensuring regular inspection of the engine).
This solution aims at eliminating the above mentioned drawbacks.
the first configuration of the claimed invention is aimed at increasing cleanliness, reducing size and weight, and also reducing hydraulic resistance along the dust removal path of the dust guard.
Said task is solved in that the anti-dust device of the engine comprises a cyclone fixed between an external and an internal cyclone panel forming a dust extraction passage, according to the claimed invention the arrangement of the cyclone and the passage cross-section for the extracted dust concentration are related by the following geometrical relations:
L1(1 to 2) DMaximum of；
H1(0 to 2) DMaximum of；
L2(0 to 2) L1；
H2(1 to 4) DMaximum of；
α is 0 to 15 °;
F is 5n to 20n,
in the formula L1Is the distance between adjacent cyclone axes in the direction of flow;
L2Is the distance between the axes of adjacent cyclones in the main row and adjacent rows in the direction of flow;
H1The distance between the axes of adjacent rows of cyclones;
H2is the distance between adjacent groups of rows;
DMaximum ofis the maximum diameter of the cyclone;
α is the angle between the rows of cyclones;
F is the cross-sectional area of the dust removal hole or passage;
n is the number of cyclones in the group belonging to the hole or channel.
Thus, the combination of the above features allows for a reduction in hydraulic resistance along the dust removal path, an increase in cleanliness due to the uniform extraction of dust concentration from each cyclone, and a reduction in the size and weight of the dust protection device due to the optimal arrangement of the cyclones.
In addition to the increased cleanliness, the reduced size and weight of the dust protection device and the reduced hydraulic resistance along the dust extraction path, a second configuration task of this invention is to adapt the dust protection device to engines with frontal air intake and to provide ease of operation while maintaining the above parameters.
said task is solved in that the anti-dust device of the aircraft engine comprises a cyclone fixed between an external and an internal cyclone panel forming a dust extraction passage, according to the claimed invention the cyclone panel forming a housing elongated along the engine axis with an inwardly disposed front cyclone panel. A fairing is arranged inside the shell on the rear wall of the dustproof device, the external hinge system structure ensures the shell rotation of the dustproof device,
the arrangement of the cyclones and the channel cross-section for extracting the dust concentration are related by the following geometrical relationship:
L1(1 to 2) DMaximum of；
H1(0 to 2) Dmaximum of；
L2(0 to 2) L1；
H2(1 to 4) DMaximum of；
α is 0 to 15 °;
F is 5n to 20n,
in the formula L1Is the distance between adjacent cyclone axes in the direction of flow;
L2Is the distance between the axes of adjacent cyclones in the main row and adjacent rows in the direction of flow;
H1The distance between the axes of adjacent rows of cyclones;
H2is the distance between adjacent groups of rows;
DMaximum ofIs the maximum diameter of the cyclone;
α is the angle between the rows of cyclones;
F is the cross-sectional area (square mm) of the dust removing port or passage;
n is the number of cyclones in the group belonging to the hole or channel.
in a second configuration of the dust-protection device, in order to reduce the hydraulic resistance along the engine path, the front cyclone panel recessed in the casing is fitted with a convergent air duct which excludes the influence of the airflow through the radial cyclone on the airflow through the front cyclone; there is also a cowling mounted at the exit of the dust guard which reduces the formation of vortices at the engine inlet and ensures the possibility of adjustment in all directions to ensure coaxiality of the dust guard with the engine. This solution makes it possible to improve the characteristics of the dust protection with the casing elongated along the engine axis.
The cyclone panels recessed into the housing also secure the shield deployment position, and avoid damage to the front cyclone panels when they collide with birds.
the claimed dust guard configuration is explained by the following figures, wherein:
Figure 1, a view of an installed cyclone and panel space;
FIG. 2a, a single row of cyclones;
FIG. 2b, cyclone bank;
FIG. 3 is a full view of the dust guard;
Figure 4, geometry of cyclone arrangement;
FIG. 5a, angular arrangement of cyclones, single row;
FIG. 5b, angular arrangement of cyclones, gang;
FIG. 6 is a full sectional view of the dust guard;
FIG. 7 is a rear wall view of the dust guard;
Fig. 8, dust guard in open position.
The engine dust guard in the first configuration (not shown) and the second configuration comprises a cyclone 1 (fig. 1) fixed between outer 2 and inner 3 cyclone panels forming an extraction dust passage.
the cyclones 1 are arranged in a single row in figure 2a or adjacent rows in figure 2 b. The adjacent rows are several rows that are closely coupled and form a group of rows. The optimum configuration is a staggered arrangement of cyclones in two adjacent rows fig. 2b which allows to ensure an optimum filling of the dust guard area and an even extraction of dust concentrate from each cyclone (1).
the cyclone rows are oriented as much as possible in the direction of the airflow drawn by the dust removal source (ejector or fan), an example of which is shown in fig. 3, where the airflow is represented by thin arrows. The dimensions between cyclones and between rows are related in the following ranges and ratios (fig. 4):
L1(1 to 2) Dmaximum of(more preferably, L11 to 1.2DMaximum of)；
H1(0 to 2) Dmaximum of(more preferably, the value is H)1(0.5 to 1) DMaximum of)；
L2(0 to 2) L1(more preferably, L2＝0.5L1)；
H2(1 to 4) DMaximum of(more preferably, the value is H)2(1.2 to 2) Dmaximum of)；
In the formula L1Is the distance between adjacent cyclone axes in the direction of flow;
L2Is the distance between the axes of adjacent cyclones in the main row and adjacent rows in the direction of flow;
H1The distance between adjacent rows of axes of cyclones to form a group of rows;
H2Is the distance between adjacent groups of rows;
Dmaximum ofthe maximum diameter of the cyclone (vortex or discharge tube).
if the distance between rows is H2>3DMaximum ofThe length of the L rows (fig. 2a, 2b) does not affect the cleanliness of the dust guard and is determined by the size and shape of the dust guard.
At Dmaximum of≤H2<3DMaximum ofIn the case of (2D), the cyclone row length is located atMaximum of≤L≤60DMaximum ofwithin the range.
The rows 4 of cyclones 1 (fig. 3, 5a, 5b) may also have an angular arrangement. The choice between the parallel and angular arrangement of the rows of cyclones (1) depends on the geometry of the dust guard and the optimum filling of the dust guard area. For example, the angular arrangement of the cyclones 1 in the cyclone panel forms a housing 5 (second order) elongated along the engine axisTwo configurations) fig. 3 or cyclone rows have a large length L and a small distance H2Is advantageous. In this case, the cyclone 1 angular point is located on the opposite side of the dust removal source, and in the most shaded region, the cyclone rows are oriented with the dust removal source along the dust concentration flow, and the farther the cyclone rows are from the dust removal source, the greater the angle between the rows.
The angles between the rows of cyclones are in the range of 0 to 15 deg. (more preferably 0.5 to 2 deg.) in fig. 5a, 5 b.
Since a force-bearing frame intercepting the dust-concentrating free passage from the cyclone 1 to the dust removal source (not shown) is required in the design of the dust-proof device, the arrangement of the cyclones 1 should be broken down into sections 6 and 7 (multi-row groups of different designs) (fig. 3).
Due to this design feature, the force-bearing formations serve to draw the dust path, i.e. the force-bearing formations in the dust guard housing 5 are arranged so that they act as a channel 8, fig. 6, through which the extraction of dust concentration from the cyclone (1) to the dust removal source is effected.
to ensure that dust is extracted evenly from each group 6, 7 or row 4 of cyclones 1, there are dust extraction holes 9 in the force-bearing plate fig. 6. The holes may be of any shape and the area of one hole (in square millimetres) lies in the range of from 5n to 20n (preferably from 8 to 15n) where n is the number of cyclones 1 in the bank or row associated with the hole 9. Typically the dust extraction apertures 9 are arranged between the rows of cyclones 1.
in addition to the number of cyclones 1 in the extraction set, the area of the dust extraction aperture 9 depends on the distance of the set from the dust removal source, i.e. the further a set of cyclones 1 is from the dust removal source, the larger the area of the aperture 9, and vice versa, the closer a set is to the dust removal source, the smaller the area.
The area of the holes 9 also depends on the direction of the extracted air flow. In the case where the apertures 9 are directed along the extracted airflow, their area should be less than the area of the apertures 9 in a set of the same number of cyclones 1 at an angle to the extracted airflow.
Figure 3 shows a second configuration of the inventive dust guard which is made in the form of a cyclone panel as in figure 1. The cyclone panels form an elongated housing 5 along the engine axis, fig. 3, with inwardly disposed front cyclone panels 10, fig. 6, fitted with converging air ducts 11. This arrangement of the front cyclone panels 10 with the converging air ducts 11 eliminates the effect of the airflow through the radial cyclones 1 on the airflow through the front cyclones 1 and also secures the position of the shield 12 in which it is deployed in figure 6. Thus, when a bird strikes the shield 12, there is sufficient space for the shield to deform and maintain a guaranteed gap to the front cyclone panel 10, thereby avoiding damage to the cyclone panel upon frontal collision with the bird.
At the exit of the dust guard, inside the casing 5 there is a fairing 13 (fig. 6, 7) which is adjustable in all directions to ensure the coaxiality of the dust guard with the engine. The cowling 13 reduces vortex formation at the engine inlet.
the claimed dust protection has a hydraulic resistance ξ irrespective of the protective screen 12dust-proof device＝ξCyclone separatora water column of +/-10 to 20 mm in height and providing a degree of cleanliness etaDust-proof device＝ηcyclone separator- (2 to 3)%, wherein ξCyclone separatorIs the resistance, eta, of a cyclone 1Cyclone separatorIs the cleanliness of one cyclone 1.
in the claimed invention, the lack of operational convenience (particularly ensuring regular inspection of the engine) is ensured by the possibility of rotation of the dust guard housing (5). The hinge system for fixing and opening the dust-protection consists of two hinges 15, fig. 7, a spring-loaded bracket 16 as a third support point and an opening and closing system 17 with a telescopic handle.
to ensure sealing, the structure has a rubber seal 14, fig. 6, 7, located on the rear wall of the dust guard and preventing dust air from bypassing the dust guard and entering the engine inlet.
the working principle of the dust-proof device is as follows.
Aircraft gas turbine engines produce a vacuum when operating. The air flow entering the engine inlet carries a suspension of dust, sand and other foreign matter. The suspended particles are subjected to a rotational motion by the cyclone 1 and move along the inner wall of the cyclone 1 under centrifugal force to rush into an extraction dust passage 8 formed between the cyclone panels at the outside 2 and inside 3 of the cyclone. There is the necessary vacuum created in the extraction dust path with the dust removal source, which facilitates further action of dust separation within the cyclone and dust concentration to the dust removal source. The dust guard of the second configuration can be opened by means of a telescopic handle 17. The handle (not shown) may be extended downward by a spring mechanism that pushes the handle (not shown). After the handle is rotated clockwise, the hook (not shown) on the shaft of the telescoping handle secured to the body is disengaged from the ear hole (not shown) secured to the rear wall of the dust guard. After the lock is opened, the dust guard is rotated on its hinge 15 up to an angle of 90 ° fig. 8.
Claims (2)
1. A dust protection arrangement for an engine comprising a cyclone fixed between outer and inner cyclone panels forming a dust extraction passageway, characterised in that the cyclone arrangement and the channel cross-section for extracted dust concentration are related by the geometric relationship:
L1(1 to 2) Dmaximum of；
H1(0 to 2) Dmaximum of；
L2(0 to 2) L1；
H2(1 to 4) DMaximum of；
α is 0 to 15 °;
f is 5n to 20n,
In the formula
L1Is the distance between adjacent cyclone axes in the direction of flow;
L2Is the distance between the axes of adjacent cyclones in the main row and adjacent rows in the direction of flow;
H1the distance between the axes of adjacent rows of cyclones;
H2Is the distance between adjacent groups of rows;
DMaximum ofis the maximum diameter of the cyclone;
α is the angle between the rows of cyclones;
F is the cross-sectional area of the dust removal hole or passage;
n is the number of cyclones in the group belonging to the hole or channel.
2. a dust-proof device of engine, comprising a cyclone fixed between an external cyclone panel and an internal cyclone panel forming a dust-removing passage, characterized in that the cyclone panel forms a casing extending along the axis of the engine, the casing has a front cyclone panel arranged inwards, and a fairing is arranged in the casing on the back wall of the dust-proof device; the external hinge system arrangement ensures that the housing of the dust-tight arrangement rotates, the arrangement of the cyclones and the channel cross-section for extracting dust concentrations are related by the following geometrical relations:
L1(1 to 2) DMaximum of；
H1(0 to 2) Dmaximum of；
L2(0 to 2) L1；
H2(1 to 4) Dmaximum of；
α is 0 to 15 °;
F is 5n to 20n,
In the formula
L1Is the distance between adjacent cyclone axes in the direction of flow;
L2Is the distance between the axes of adjacent cyclones in the main row and adjacent rows in the direction of flow; h1The distance between the axes of adjacent rows of cyclones;
H2is the distance between adjacent groups of rows;
DMaximum ofIs the maximum diameter of the cyclone;
α is the angle between the rows of cyclones;
F is the cross-sectional area of the dust removal hole or passage;
n is the number of cyclones in the group belonging to the hole or channel.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2016110040 | 2016-03-21 | ||
| RU2016110040A RU2638692C2 (en) | 2016-03-21 | 2016-03-21 | Engine dust-protecting device (versions) |
| PCT/RU2016/000688 WO2017164768A1 (en) | 2016-03-21 | 2016-10-11 | Engine dust-protection device (variants) |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108699969A CN108699969A (en) | 2018-10-23 |
| CN108699969B true CN108699969B (en) | 2019-12-17 |
Family
ID=59900686
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680078646.9A Active CN108699969B (en) | 2016-03-21 | 2016-10-11 | Dust-proof device of engine |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN108699969B (en) |
| RU (1) | RU2638692C2 (en) |
| WO (1) | WO2017164768A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2742697C1 (en) * | 2020-06-15 | 2021-02-09 | Юрий Яковлевич Ситницкий | Air intake device for helicopter gas turbine engine, removing particles of sand and dust from air |
| RU2752446C1 (en) * | 2020-10-20 | 2021-07-28 | Юрий Яковлевич Ситницкий | Air intake device of helicopter gas turbine engine |
| RU2752445C1 (en) * | 2020-10-20 | 2021-07-28 | Юрий Яковлевич Ситницкий | Air intake device of helicopter gas turbine engine that removes sand and dust particles from air |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2174616C2 (en) * | 1999-09-21 | 2001-10-10 | Государственное унитарное предприятие "Завод им. В.Я. Климова" - дочернее предприятие государственного унитарного предприятия Военно-промышленный комплекс "МАПО" | Intake unit for turboprop engine |
| RU2181439C2 (en) * | 1999-11-22 | 2002-04-20 | Открытое акционерное общество "Всероссийский научно-исследовательский институт транспортного машиностроения" | Dust-protection device for flying vehicle engine |
| RU2414611C2 (en) * | 2009-05-04 | 2011-03-20 | Закрытое акционерное общество "Объединенные газопромышленные технологии "Искра-Авигаз" (ЗАО "Искра-Авигаз") | Complex air cleaning device |
| RU2523706C1 (en) * | 2013-04-24 | 2014-07-20 | Владимир Николаевич Абрамов | Wind-driven power plant |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3483676A (en) * | 1967-09-29 | 1969-12-16 | Gen Electric | Helicopter engine air inlets |
| FR2250671B1 (en) * | 1973-11-09 | 1980-01-04 | Aerospatiale |
-
2016
- 2016-03-21 RU RU2016110040A patent/RU2638692C2/en active
- 2016-10-11 CN CN201680078646.9A patent/CN108699969B/en active Active
- 2016-10-11 WO PCT/RU2016/000688 patent/WO2017164768A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2174616C2 (en) * | 1999-09-21 | 2001-10-10 | Государственное унитарное предприятие "Завод им. В.Я. Климова" - дочернее предприятие государственного унитарного предприятия Военно-промышленный комплекс "МАПО" | Intake unit for turboprop engine |
| RU2181439C2 (en) * | 1999-11-22 | 2002-04-20 | Открытое акционерное общество "Всероссийский научно-исследовательский институт транспортного машиностроения" | Dust-protection device for flying vehicle engine |
| RU2414611C2 (en) * | 2009-05-04 | 2011-03-20 | Закрытое акционерное общество "Объединенные газопромышленные технологии "Искра-Авигаз" (ЗАО "Искра-Авигаз") | Complex air cleaning device |
| RU2523706C1 (en) * | 2013-04-24 | 2014-07-20 | Владимир Николаевич Абрамов | Wind-driven power plant |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2638692C2 (en) | 2017-12-15 |
| RU2016110040A (en) | 2017-09-26 |
| WO2017164768A1 (en) | 2017-09-28 |
| CN108699969A (en) | 2018-10-23 |
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