CN110617149A - Integral inertia particle separator - Google Patents
Integral inertia particle separator Download PDFInfo
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- CN110617149A CN110617149A CN201910796022.6A CN201910796022A CN110617149A CN 110617149 A CN110617149 A CN 110617149A CN 201910796022 A CN201910796022 A CN 201910796022A CN 110617149 A CN110617149 A CN 110617149A
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- outer shell
- channel
- section
- particle separator
- central body
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Classifications
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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 discloses an integral inertia particle separator, which comprises an outer shell, a flow divider and a central body, wherein the front half section of the central body and the front half section of the outer shell surround to form an air inlet channel, the rear half section of the central body and the inner wall of the flow divider surround to form a main channel, and the rear half section of the outer shell and the outer wall of the flow divider surround to form a clearing channel. The V-shaped channel with a certain winding angle is designed on the inner wall surface of the outer shell, so that when particles entering the particle separator impact the outer shell, the particles do not impact on a smooth wall surface, but the wall surface of the V-shaped channel enables the incident and rebound tracks of the particles to be changed into three-dimensional tracks from two-dimensional tracks in an axial-radial plane, the particles move along the outer shell, the particles are difficult to return to a main flow channel under the condition of not changing the rebound speed and the height of the outer shell, the particles are discharged out of the separator along a clearing flow channel, and the separation efficiency of the particles is improved on the premise of not damaging the aerodynamic performance.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to an integral inertia particle separator in a helicopter engine.
Background
The helicopter can take off, land and hover at any place without the limitation of terrain and ground objects. However, due to the effect of the rotor wing downwash, a great amount of dust is often rolled up by the helicopter in the stage of taking off and landing, and the sucked dust can bring great harm to the working efficiency and the use reliability of a power system (a turboshaft engine): the sucked sand dust can accelerate the abrasion of the engine blade; blocking tiny cooling air channels in the engine; deposition on turbine blades disrupts their stable operation. This leads to deterioration of engine performance, i.e., reduction in power and increase in fuel consumption, and ultimately leads to a reduction in the service life of the engine. Therefore, a protective device must be used to block the sand and dust.
Practice has shown that the lifetime of an engine with a particle separator installed is improved by a factor of 10 or more than the lifetime of an engine without a particle separator installed. The common sand and dust protection devices applied to the turboshaft engine comprise a blocking type particle separator, a multi-tube type inertia particle separator and an integral type particle separator. The volume and the weight of the barrier type particle separator are large, the filter needs to be cleaned frequently, or the total pressure loss of the barrier type particle separator is increased; the multi-tube particle separator has heavy weight and large windward area, is difficult to perform anti-icing design, and needs extra power for scavenging air and discharging sand; the integral particle separator has the advantages of simple structure, good integrity, light weight, high separation efficiency and small flow loss, and is a mainstream sand separating device at present. The integral particle separator utilizes different inertia forces generated when gas-solid two-phase flow is bent in the bent flow channel to throw solid-phase particles with larger inertia force to the outer layer of the fluid, so that the particles are collected and discharged from the cleaning flow channel; in fact, many large-particle-size particles thrown to the outer layer of the fluid collide with the inner wall surface of the outer shell and rebound back into the fluid, so that part of the particles return to the main stream, and the separation efficiency is reduced.
Therefore, a new technical solution is needed to solve the above problems.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides an integral inertial particle separator with a specific wall surface shape, which aims to solve the problem that particles in the particle separator collide with the wall surface to rebound and effectively improve the separation efficiency of the separator on the premise of not changing other size changes of the separator.
The technical scheme is as follows: in order to achieve the purpose, the invention can adopt the following technical scheme:
an integral inertia particle separator comprises an outer shell with a circular cross section, a central body which is positioned in the outer shell and is coaxial with the outer shell, and a flow divider positioned between the outer shell and the central body; the front half section of the central body and the front section of the outer shell form an air inlet channel; the rear half section of the central body and the inner wall of the flow divider enclose a main flow passage, and the rear section of the outer body and the outer wall of the flow divider form a clearing flow passage for discharging separated particles; the inner wall and the outer wall of the flow divider form an included angle to enable the main flow channel and the cleaning flow channel to mutually and independently extend backwards; the structure is characterized in that the inner wall surface of the outer shell is provided with a circle of parallel channels which extend in the same shape around the inner wall surface; the cross section of the channel is V-shaped, and an acute included angle is formed between the extending direction of the inner wall surface of each channel and the central symmetry axis of the outer shell.
Has the advantages that: .
Further, an included angle formed between the extending direction of the inner wall surface of each channel and the central symmetry axis of the outer shell is set as a winding angle theta which is 20 degrees.
Furthermore, a middle section of the outer shell is arranged between the front section and the rear section of the outer shell, the middle section of the outer shell protrudes outwards, and the longitudinal section of the middle section of the outer shell is in an arc shape protruding outwards; the middle section of the central body corresponding to the middle section of the outer shell extends convexly towards the outer shell, and the cross section of the middle section of the central body which extends convexly is also arc-shaped; the narrowest part of the cross section formed between the middle section of the outer shell and the middle section of the central body is a throat, and the cross section area of the inlet of the air inlet channel is gradually reduced to the cross section area of the throat; the inlet of the main runner and the inlet of the clearing runner are communicated with the tail end of the air inlet channel at the same time, and the sectional area of the throat to the sectional area of the tail end of the air inlet channel is gradually increased.
Furthermore, a bulge protruding towards the outer shell is arranged at the middle section of the central body at the throat of the air inlet.
Furthermore, the circumferential angle of the width of the single channel is beta, the inner wall surface of the outer shell 1 takes the beta angle as an interval, and 360/beta channels are uniformly distributed around the central symmetry axis of the outer shell in the circumferential direction.
Further, the circumferential angle alpha of the half groove width of the groove channel is 0.5 degrees, and the deepest part of the groove depth h of the groove channel is 1.6 mm.
Further, the groove depth h at the beginning end of the groove channel is 0, the groove depth h is gradually increased along with the extending direction of the groove channel until the groove depth is the deepest and keeps constant, and the groove depth h is gradually reduced to 0 when the groove depth is about to reach the ending end of the groove channel.
Further, all the grooves are serrated along the axial section.
Drawings
FIG. 1 is an axial-symmetric plan sectional view of an integral inertial particle separator of the present invention.
FIG. 2 is an enlarged partial view of the V-shaped channel of the present invention taken perpendicular to the plane of the axis of symmetry and on the inside wall of the housing.
FIG. 3 is a three-dimensional schematic view of the outer housing of the present invention with the center body and splitter removed from the shield.
FIG. 4 is a schematic semi-sectional view of the outer housing of the present invention with the center body and splitter removed.
FIG. 5 is an enlarged view of a portion of the throat of the inventive inlet.
Detailed Description
At present, the integral particle separator has the advantages of simple structure, good integrity, light weight, high separation efficiency and small flow loss. In an integral inertial particle separator, the trajectory of the sand in the flow field is determined by the drag of the air flow on the particles, the centrifugal force caused by the sharp turn of the air flow, the self-gravity and the collision of the particles with the wall surface. When the gas flow containing the particles turns in the flow channel, the particles in the solid phase are not turned to the inside together with the gas flow due to inertia and centrifugal force, and are thrown off and collected to the outside, and are discharged from the cleaning flow channel together with the outside gas flow.
Collisions can cause abrupt changes in particle trajectories and thus affect particle motion. The current optimization of particle separation usually considers the design of the overall shape of a flow channel so as to increase the centrifugal force borne by the particles; or coatings with different rebound properties are adopted in the wall surface area where the particles collide to control the rebound track, and the like;
theoretically, the integral inertial particle separator without prerotation has no velocity component in the tangential direction, so that when the motion trajectory of the particles is considered, the default trajectory is a two-dimensional motion trajectory in a section passing through the central axis, and therefore, the situation that the particle rebound trajectory introduces the tangential velocity under the condition that the particle incidence condition and the rebound property of the collision wall surface are not changed by some means can be considered, so that the projection of the rebound angle on the section passing through the central axis is reduced, the particle rebound angle is reduced, the risk that the particles enter the main flow channel 8 is reduced, and the sand-dust separation efficiency is improved.
Referring to fig. 1, the present invention relates to an integral inertial particle separator, which comprises an outer casing 1 with a circular cross section, a central body 3 disposed in the outer casing 1 and coaxial with the outer casing 1, and a flow divider 2 disposed between the outer casing 1 and the central body 3. The front half section of the central body 3 and the front section of the outer body 1 are combined to form an air inlet channel 6 of the particle separator, the rear half section of the central body 3 and the inner wall 21 of the flow divider 2 are combined to form a main channel 8 for providing clean air flow for the compressor, and the rear half section of the outer body 1 and the outer wall 22 of the flow divider 2 form a clearing channel 7 for discharging separated particles; the inner wall 21 of the flow divider 2 forms an angle with the outer wall 22 extending the main flow channel backwards independently of the scavenging flow channel. The inner wall surface of the outer casing is provided with side-by-side channels 4 extending in the same shape around the inner wall surface in one turn. The cross section of the channel 4 is V-shaped, and each channel 4 forms an acute included angle theta between the extending direction of the inner wall surface and the central symmetry axis 9 of the outer shell 1.
The first key of the invention is that the inner wall surface of the outer shell 1 is provided with a V-shaped channel 4. Referring to fig. 2, 3 and 4, a V-shaped channel 4 is formed on the inner wall surface of the outer casing 1; the circumferential angle of the width of the single V-shaped channel 4 is beta, which is 1 degree in the embodiment; the circumferential angle of the half groove width of the V-shaped groove 4 is alpha, in the embodiment, the circumferential angle is 0.5 degrees, the groove depth of the V-shaped groove 4 is h, and in the embodiment, the h is 1.6 mm; the single V-groove 4 has a certain winding angle theta. Taking rifling of the inner wall surface of a gun as an example, in the prior art, the rifling is a spiral groove which is manufactured on the inner surface of a gun barrel and has a certain inclination angle with the axis of the barrel, the inclination angle of the rifling to the axis of the gun barrel is called a winding angle, in the invention, the winding angle theta is defined as an included angle between a single V-shaped channel 4 and a symmetrical shaft 9 of an integral inertia particle separator, and in the embodiment, the winding angle theta is 20 degrees; 360/beta V-shaped grooves 4 are uniformly distributed on the inner wall surface of the outer shell 1 at intervals of beta angles in the circumferential direction around the symmetry axis 9; the control parameters of the V-shaped channel 4 are optimized and determined according to the particle size and the flow velocity of the air flow.
Referring to fig. 5, in order to smoothen the inner wall surface of the outer casing 1, the groove depth h at the channel starting end 41 is 0, and gradually increases along with the channel extending direction until reaching the deepest position and keeping a section of the groove depth constant, and the groove depth h gradually decreases to 0 when reaching the channel ending end 42.
Controlling the change rate of the area in the flow channel along the flow path; the second key of the invention is to optimize the change rule of the included angle between the flow direction and the axial direction, the change rule of the radius of the profile of the central body 3 along the axial direction and the local curvature of the profile of the central body 3. Referring to fig. 1, the flow channel design is mainly divided into four parts:
the first part is from the inlet 61 to the throat 10 of the inlet, and a small bulge 5 is arranged at the throat 10 of the inlet. The partial channel area (shown as width in a two-dimensional diagram in fig. 1) gradually decreases along the flow path to reach a minimum in the inlet 6 at the inlet throat 10, where the mach number reaches a maximum in the inlet 6; in the part, the change situation of the radius of the center line of the flow passage area along the axial direction is quadratic curve increase; the included angle between the airflow direction and the axial direction at the air inlet passage throat 10 reaches the maximum at the air inlet passage throat 10; the purpose is to increase the particle speed and improve the particle separation capability;
the second portion is from the inlet throat 10 to the purge flowpath inlet 71, the primary flowpath inlet 81. The area of the part of the flow passage is gradually increased along the flow path; the change of the radius of the central line of the flow area behind the inlet channel throat 10 along the axial direction is as follows: under the constraint of tangency of the central lines of the flow passage areas of the first part and the second part, the flow direction of the air flow is reduced according to a quadratic curve, and the included angle between the flow direction of the air flow and the axial direction is greatly deflected. The purpose is that under the condition of expanding the area of the flow channel, the radius of the central line of the area of the flow channel is changed according to the change, the width of the part of the flow channel can be compressed, and the width of the part of the flow channel can be changed according to the approximately constant-expansion rule after the air inlet channel throat 10, because when the radial distance of the particles with stronger following flow passing through from the inner air flow to the outer air flow due to the centrifugal force is fixed, the proportion of the particles with stronger following flow reaching the outer layer fluid is increased, and when the scavenging ratio is fixed, the separation efficiency of the particles with stronger following flow can be improved; the section has a great deflection towards the inside in the flow direction behind the throat, and the centrifugal force borne by the particles with stronger fluidity at the position can be enhanced by combining the deflection angle of the atmospheric flow of the second part, the section has a longer flow design, the aim is that the sand separation process of the particles with stronger fluidity is mainly carried out at the part, and the increase of the flow direction length is beneficial to fully exerting the capability of the particles with stronger fluidity to pass through to the outer layer airflow;
the third portion is from the primary channel inlet 81 to the primary channel outlet 82. The change rate of the area of the part can be obtained according to the Mach number from the inlet 81 of the main runner to the outlet 82 of the main runner and the fluid mechanics principle so as to ensure that the flow speed of the part changes continuously and reduce the aerodynamic loss of the airflow in the part, and the radius of the center line of the area of the runner is designed according to the change rule of the flow speed which is firstly rapid and then slow;
the fourth portion is from the primary flowpath inlet 81 to the purge flowpath outlet 72. The change rate of the partial area is designed to be gradually reduced, and the radius of the center line of the flow passage area is designed according to the slow and fast equivalent change rule:
the schematic diagram of the invention is illustrated by taking an air inlet system of an aircraft engine as an example, and the invention is also applicable to other application scenes. The above-described embodiments are intended to be illustrative of the present invention and are not to be construed as limiting the invention. Therefore, all embodiments with the same design concept are within the protection scope of the present invention.
The invention embodies a number of methods and approaches to this solution and the foregoing is only a preferred embodiment of the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.
Claims (8)
1. The integral inertial particle separator comprises an outer shell with a circular cross section, a central body which is positioned in the outer shell and is coaxial with the outer shell, and a flow divider positioned between the outer shell and the central body; the front half section of the central body and the front section of the outer shell form an air inlet channel; the rear half section of the central body and the inner wall of the flow divider enclose a main flow passage, and the rear section of the outer body and the outer wall of the flow divider form a clearing flow passage for discharging separated particles; the inner wall and the outer wall of the flow divider form an included angle to enable the main flow channel and the cleaning flow channel to mutually and independently extend backwards; the structure is characterized in that the inner wall surface of the outer shell is provided with a circle of parallel channels which extend in the same shape around the inner wall surface; the cross section of the channel is V-shaped, and an acute included angle is formed between the extending direction of the inner wall surface of each channel and the central symmetry axis of the outer shell.
2. The integral inertial particle separator of claim 1 wherein: an included angle formed between the extending direction of the inner wall surface and the central symmetry axis of the outer shell of each channel is set as a wrapping angle theta which is 20 degrees.
3. The integral inertial particle separator of claim 1 wherein: the middle section of the outer shell is arranged between the front section and the rear section of the outer shell, the middle section of the outer shell protrudes outwards, and the longitudinal section of the middle section of the outer shell is in an outward-protruding arc shape; the middle section of the central body corresponding to the middle section of the outer shell extends convexly towards the outer shell, and the cross section of the middle section of the central body which extends convexly is also arc-shaped;
the narrowest part of the cross section formed between the middle section of the outer shell and the middle section of the central body is a throat, and the cross section area of the inlet of the air inlet channel is gradually reduced to the cross section area of the throat;
the inlet of the main runner and the inlet of the clearing runner are communicated with the tail end of the air inlet channel at the same time, and the sectional area of the throat to the sectional area of the tail end of the air inlet channel is gradually increased.
4. The integral inertial particle separator of claim 1 wherein: and a bulge protruding towards the outer shell is arranged at the middle section of the central body at the throat of the air inlet.
5. The integral inertial particle separator of claim 1 or 2 wherein: the circumferential angle of the width of the single channel is beta, the inner wall surface of the outer shell 1 takes the beta angle as an interval, and 360/beta channels are uniformly distributed around the central symmetry axis of the outer shell in the circumferential direction.
6. The integral inertial particle separator of claim 3 wherein: the circumferential angle alpha of the half groove width of the groove channel is 0.5 degrees, and the deepest part of the groove depth h of the groove channel is 1.6 mm.
7. The integral inertial particle separator of claim 4 wherein: the groove depth h at the starting end of the groove channel is 0, the groove depth h is gradually increased along with the extending direction of the groove channel until the groove depth is the deepest and keeps constant, and the groove depth h is gradually reduced to 0 when the groove depth is about to reach the ending end of the groove channel.
8. The integral inertial particle separator of claim 2 wherein: all the grooves are serrated along the axial section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910796022.6A CN110617149A (en) | 2019-08-27 | 2019-08-27 | Integral inertia particle separator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910796022.6A CN110617149A (en) | 2019-08-27 | 2019-08-27 | Integral inertia particle separator |
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| CN110617149A true CN110617149A (en) | 2019-12-27 |
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| CN201910796022.6A Pending CN110617149A (en) | 2019-08-27 | 2019-08-27 | Integral inertia particle separator |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111844799A (en) * | 2020-07-22 | 2020-10-30 | 江苏新扬新材料股份有限公司 | Forming method of aviation particle separator |
| CN113530857A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Electric driving type sand discharging device for particle separator of aircraft engine |
| US11834988B1 (en) | 2022-06-15 | 2023-12-05 | Rolls-Royce North American Technologies Inc. | Turbine engine inertial particle separator with particle rebound suppression |
| US11834989B1 (en) | 2022-06-15 | 2023-12-05 | Rolls-Royce Corporation | Gas turbine engine inlet particle separators with coatings for rebound control |
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| CN103174521A (en) * | 2011-12-21 | 2013-06-26 | 通用电气公司 | Gas turbine engine particle separator |
| EP3067531A1 (en) * | 2015-03-10 | 2016-09-14 | Rolls-Royce North American Technologies, Inc. | Inertial particle separator flow and particle bounce control |
| US20170191503A1 (en) * | 2016-01-06 | 2017-07-06 | Honeywell International Inc. | Inlet particle separator system with high curvature hub |
| CN106988886A (en) * | 2016-01-21 | 2017-07-28 | 通用电气公司 | Inlet particle separators for turbogenerator |
| CN109519282A (en) * | 2018-11-07 | 2019-03-26 | 中国航发湖南动力机械研究所 | Monoblock type Inertia particle separator and aero-engine based on bounce-back characteristic |
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2019
- 2019-08-27 CN CN201910796022.6A patent/CN110617149A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6508052B1 (en) * | 2001-08-01 | 2003-01-21 | Rolls-Royce Corporation | Particle separator |
| CN103174521A (en) * | 2011-12-21 | 2013-06-26 | 通用电气公司 | Gas turbine engine particle separator |
| EP3067531A1 (en) * | 2015-03-10 | 2016-09-14 | Rolls-Royce North American Technologies, Inc. | Inertial particle separator flow and particle bounce control |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111844799A (en) * | 2020-07-22 | 2020-10-30 | 江苏新扬新材料股份有限公司 | Forming method of aviation particle separator |
| CN111844799B (en) * | 2020-07-22 | 2022-03-29 | 江苏新扬新材料股份有限公司 | Forming method of aviation particle separator |
| CN113530857A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Electric driving type sand discharging device for particle separator of aircraft engine |
| US11834988B1 (en) | 2022-06-15 | 2023-12-05 | Rolls-Royce North American Technologies Inc. | Turbine engine inertial particle separator with particle rebound suppression |
| US11834989B1 (en) | 2022-06-15 | 2023-12-05 | Rolls-Royce Corporation | Gas turbine engine inlet particle separators with coatings for rebound control |
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Application publication date: 20191227 |
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