CN113123879B - Air entraining layout for weakening dissipation vortex in front of grate disc - Google Patents
Air entraining layout for weakening dissipation vortex in front of grate disc Download PDFInfo
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- CN113123879B CN113123879B CN202110323485.8A CN202110323485A CN113123879B CN 113123879 B CN113123879 B CN 113123879B CN 202110323485 A CN202110323485 A CN 202110323485A CN 113123879 B CN113123879 B CN 113123879B
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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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a bleed air layout for weakening dissipation vortexes in front of a grate disc, wherein a plurality of prewhirl nozzles are circumferentially arranged at the upstream position of the grate disc on the surface of a stator drum as bleed air inlets, so that air flow introduced by the bleed air inlets is mixed with radially inward-flowing air flow, the cooling quality can be improved, the air flow can continuously flow downstream, the cooling effect on the grate disc and downstream components is improved, the dissipation vortexes in front of the grate disc can be impacted, the dissipation vortexes are weakened or even destroyed, the active control on the flow structure in a rear shaft diameter conical wall cavity of a compressor is realized, the dissipation vortexes in front of the grate disc are not easily formed, the wind resistance and temperature rise in front of the grate disc is further reduced, and the cooling quality is improved.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a bleed air layout for weakening dissipation vortex in front of a grate disc.
Background
With the continuous improvement of the performance of the aircraft engine, the temperature before the turbine is higher and higher, which puts higher requirements on the level of material technology and aircraft engine air system cooling technology. At present, the application of aeroengine material technology tends to be in an extreme state, the technology cannot meet all design requirements only by high-temperature material technology, and the rest cooling requirements are realized by depending on an aeroengine air system. Generally, increasing the flow rate of bleed air in the air system directly improves the cooling effect of the air system, but the increase of the flow rate of the air system causes the attenuation of the overall performance of the engine, so how to reduce the entropy of the cooling air flow in the air system under the condition of ensuring the overall performance stability of the engine, thereby exploiting the overall cooling potential of the cooling air flow is the key for the successful design of the aero-engine.
In general, in order to meet the requirement of axial force adjustment, a labyrinth plate structure is installed in an air system of an aircraft engine. In order to realize the adjustment of the axial force, the labyrinth plate with a larger radius is required to be designed. The distance between the grate plate and the grate tooth at the connection part of the grate plate and the rotor is larger, so that a dead-end is formed, and gas easily forms a large-range dissipation vortex structure in the area, so that the temperature distribution in the area is rapidly deteriorated. Fig. 1 shows a conventional conical wall cavity bleed air scheme, arrows in fig. 1 indicate air flow directions, and a significant dissipation vortex structure exists in front of a grate plate 100, and numerical calculation results of the dissipation vortex structure are shown in fig. 2.
In the design of an air system of an aircraft engine, for a bleed air mode of radial internal flow in a conical wall cavity, the influence of temperature rise caused by dissipation vortex formed by upstream incoming flow in front of a grate plate is generally ignored in the traditional design. Along with the wider and wider working range and higher thrust-weight ratio of a new generation of engine, under some extremely severe working conditions, the temperature of a hot end part of the engine is higher and higher, and the key of finely designing a flow path of an air system to reduce the wind resistance temperature rise is higher and higher, so that the vortex system structure causing the temperature rise is required to be treated. However, at present, no design which has low cost and can effectively inhibit the formation of dissipation vortexes in front of the high-radius grate plate exists.
Disclosure of Invention
In view of this, the invention provides a bleed air layout for weakening dissipation vortexes in front of a grate plate, so as to effectively inhibit the dissipation vortexes in front of the grate plate.
The invention provides an air entraining layout for weakening dissipation vortex in front of a grate plate, which comprises the following steps:
on the stator drum surface opposite to the grate disc, within 8-10 mm from a first tooth positioned at the upstream of the airflow in the grate disc, a circle of bosses are arranged along the circumferential direction of the stator drum surface, and a plurality of prerotation nozzles are arranged on the bosses and used as air-entraining inlets;
the air-entraining inlet carries out pre-rotation air feeding at a space angle, the space angle of the air-entraining inlet is obtained by clockwise rotating alpha by taking the normal of the surface of the stator drum barrel and a bus of the surface of the stator drum barrel as a rotating shaft, and then anticlockwise rotating beta by taking the normal of the surface of the stator drum barrel as the rotating shaft; wherein alpha is more than or equal to 75 degrees and less than or equal to 85 degrees, beta is more than or equal to 30 degrees and less than or equal to 60 degrees.
In a possible implementation manner, in the air-entraining layout for weakening the dissipation vortex in front of the grate plate, provided by the invention, the aperture of the air-entraining inlet is in a range of 1mm to 2 mm.
In a possible implementation manner, in the bleed air layout for reducing the dissipation vortex in front of the grate plate, provided by the invention, the diameter of each pre-swirl nozzle included in the bleed air inlet is the same.
In a possible implementation manner, in the bleed air layout for reducing the dissipation vortex in front of the grate plate, provided by the invention, the number of the pre-rotation nozzles included in the bleed air inlet is 8-60.
According to the air entraining layout for weakening the dissipated vortex in front of the toothed disc, the plurality of pre-rotation nozzles are circumferentially arranged at the upstream position of the toothed disc on the cylinder surface of the stator drum and serve as the air entraining inlets, so that after air flow introduced by the air entraining inlets is mixed with air flow flowing inwards in the radial direction, the air flow can improve the cooling quality and then flows downstream continuously, the cooling effect on the toothed disc and components downstream is improved, the dissipated vortex structure in front of the toothed disc can be impacted, the dissipated vortex is weakened or even destroyed, active control on the flow structure in the cavity of the conical wall of the rear shaft diameter of the compressor is realized, the dissipated vortex structure is not easily formed in front of the toothed disc, the wind resistance and temperature rise in front of the toothed disc are reduced, and the cooling quality is improved.
Drawings
FIG. 1 is a schematic diagram of a conventional conical wall cavity bleed air scheme;
FIG. 2 is a result of numerical calculation of a dissipation vortex structure of a conventional conical wall cavity bleed air scheme;
FIG. 3 is a schematic view of a bleed air layout for reducing dissipation vortex in front of a grate plate according to the present invention;
FIG. 4 is a partial schematic view of a bleed air layout for reducing dissipation vortices in front of a grate plate according to the present invention;
fig. 5 is a schematic space angle diagram of a bleed air inlet in a bleed air layout for weakening dissipation vortexes in front of a grate plate, which is provided by the invention;
fig. 6 is a result of calculating a dissipation vortex structure value of a bleed air layout for weakening dissipation vortices in front of a grate plate.
Description of the reference numerals: the device comprises a grate disc 1, a stator drum surface 2, a bleed air inlet 3, a boss 4 and a pre-rotation nozzle 5.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only illustrative and are not intended to limit the present invention.
According to the air entraining layout for weakening the dissipated vortex in front of the grate plate, as shown in fig. 3, on the stator drum surface 2 opposite to the grate plate 1, a circle of bosses are arranged along the circumferential direction of the stator drum surface 2 within the range of 8-10 mm away from a first channel tooth (shown as a in fig. 3) positioned at the upstream of air flow in the grate plate 1, and a plurality of pre-rotation nozzles are arranged on the bosses and used as air entraining inlets 3; because the stator part is a thin-wall part, an orifice structure with a pre-rotation angle of more than 30 degrees cannot be directly chiseled on the thin-wall part to serve as a pre-rotation nozzle, therefore, in the manufacturing process of the stator part, a circle of boss 4 (shown in figure 4) is processed by adopting a turning process at the position where the pre-rotation nozzle needs to be arranged on the surface of a stator drum, a plurality of pre-rotation nozzles 5 (three pre-rotation nozzles 5 are shown in figure 4) are arranged on the boss 4 by adopting a drilling process, the specific size of the boss 4 is not clearly specified, and only the requirement of drilling needs to be met;
The bleed air inlet 3 pre-swirls air at a spatial angle, and a method for determining the spatial angle of the bleed air inlet 3 is described below, as shown in fig. 5, where the rotor rotates counterclockwise (as shown by a thick arrow in fig. 5), and assuming that a central axis of the pre-swirl nozzle 5 in an initial state is a stator drum surface normal (as shown by B in fig. 5), the pre-swirl nozzle 5 is first rotated clockwise with a stator drum surface generatrix (as shown by C in fig. 5) passing through the central axis as a rotating shaft, the rotating angle is α, the adjustable range of α is 75 ° to 85 °, then the pre-swirl nozzle 5 is rotated counterclockwise with the stator drum surface normal as the rotating shaft, the rotating angle is β, the adjustable range of β is 30 ° to 60 °, thereby obtaining a spatial angle of the bleed air inlet 3, that is, the spatial angle of the bleed air inlet 3 is a stator drum surface normal, and the bleed stator drum surface generatrix is rotated clockwise, then, the drum is rotated counterclockwise by beta by taking the normal line of the drum surface of the stator as a rotating shaft; wherein alpha is more than or equal to 75 degrees and less than or equal to 85 degrees, beta is more than or equal to 30 degrees and less than or equal to 60 degrees.
As shown in fig. 3, after the airflow introduced from the bleed air inlet 3 is mixed with the airflow flowing radially inwards (i.e. the airflow introduced from the leftmost inlet shown in fig. 3), the arrows in fig. 3 indicate the airflow direction, which not only can improve the cooling quality, but also can continue to flow downstream, improve the cooling effect on the grate plate and the downstream components, and impact the dissipation vortex structure in front of the grate plate, so as to weaken or even destroy the dissipation vortex. The numerical calculation shows that under the working condition that the flow rate of the bleed air is about 0.6kg/s, the temperature drop of the air flow at the free vortex region and the grate inlet and outlet can reach 180K, the numerical calculation result is shown in fig. 6 (the position indicated by the arrow in fig. 6 is the position of the bleed air inlet), and compared with the numerical calculation result of the traditional conical wall cavity bleed air scheme shown in fig. 2, the significant dissipation vortex structure exists in front of the grate plate in fig. 2, the dissipation vortex structure in front of the grate plate in fig. 6 is obviously weakened, and the flow state is well improved.
In the specific implementation, in the bleed air layout for weakening the dissipation vortex in front of the grate plate, provided by the invention, the aperture of the bleed air inlet is determined by the total flow rate of the bleed air of the cooling air flow, and specifically, the aperture of the bleed air inlet can be controlled within a range of 1mm to 2 mm.
Preferably, in order to ensure the balanced cooling effect of the whole conical wall, in the bleed air layout for weakening the dissipation vortex in front of the grate plate provided by the invention, the aperture of each pre-swirl nozzle included in the bleed air inlet can be designed to be the same.
In specific implementation, in the air-entraining layout for weakening the dissipation vortex in front of the grate plate, provided by the invention, the number of the pre-rotation nozzles is determined by the total flow of the air-entraining flow of the cooling air flow, and 8-60 pre-rotation nozzles can be arranged along the circumferential direction of the cylinder surface of the stator drum and serve as air-entraining inlets. Of course, the number of the pre-swirl nozzles is not limited to this range, and the number of the pre-swirl nozzles can be adjusted according to factors such as the type of the conical wall cavity and the required cooling effect, and is not limited herein.
According to the air entraining layout for weakening dissipation vortexes in front of the grate disc, the plurality of pre-rotation nozzles are circumferentially arranged at the upstream position of the grate disc on the surface of the stator drum and serve as the air entraining inlets, and after air flow introduced by the air entraining inlets is mixed with radially inward-flowing air flow, the air entraining layout can improve cooling quality, then the air flow can continuously flow downstream, so that the cooling effect on the grate disc and downstream components is improved, the dissipation vortexes in front of the grate disc can be impacted, the dissipation vortexes are weakened or even destroyed, active control over a flow structure in a conical wall cavity of a rear shaft diameter of a gas compressor is realized, the dissipation vortexes in front of the grate disc are not easily formed, the wind resistance and the temperature rise in front of the grate disc are reduced, and the cooling quality is improved.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (4)
1. The utility model provides a weaken bleed overall arrangement of grate dish place ahead dissipation vortex which characterized in that:
on the stator drum surface opposite to the grate disc, within 8-10 mm from a first tooth positioned at the upstream of the airflow in the grate disc, a circle of bosses are arranged along the circumferential direction of the stator drum surface, and a plurality of prerotation nozzles are arranged on the bosses and used as air-entraining inlets;
the air-entraining inlet carries out pre-rotation air feeding at a space angle, the space angle of the air-entraining inlet is obtained by clockwise rotating alpha by taking the normal of the surface of the stator drum barrel and a bus of the surface of the stator drum barrel as a rotating shaft, and then anticlockwise rotating beta by taking the normal of the surface of the stator drum barrel as the rotating shaft; wherein alpha is more than or equal to 75 degrees and less than or equal to 85 degrees, beta is more than or equal to 30 degrees and less than or equal to 60 degrees;
airflow introduced from the air guide inlet is mixed with airflow flowing radially inwards and then flows downstream continuously, so that the dissipation vortex structure in front of the grate plate is impacted, and dissipation vortexes are weakened or even destroyed.
2. The air-entraining layout for dissipating vortexes in front of the weakening grate plate according to claim 1, wherein the aperture of the air-entraining inlet is in a range of 1mm to 2 mm.
3. The air-entraining layout for dissipating vortex in front of the grate plate as set forth in claim 1, wherein the air-entraining inlet comprises pre-swirl nozzles having the same orifice diameter.
4. The air-entraining layout for dissipating vortex in front of the grate plate for reducing the number of the exhaust inlets according to claim 1, wherein the number of the pre-swirl nozzles included in the air-entraining inlets is 8-60.
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| CN202110323485.8A CN113123879B (en) | 2021-03-26 | 2021-03-26 | Air entraining layout for weakening dissipation vortex in front of grate disc |
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| CN202110323485.8A CN113123879B (en) | 2021-03-26 | 2021-03-26 | Air entraining layout for weakening dissipation vortex in front of grate disc |
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| CN113123879A CN113123879A (en) | 2021-07-16 |
| CN113123879B true CN113123879B (en) | 2022-06-28 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11315800A (en) * | 1998-04-30 | 1999-11-16 | Toshiba Corp | Air compressor |
| CN109139269A (en) * | 2017-06-27 | 2019-01-04 | 中国航发常州兰翔机械有限责任公司 | A kind of aero-engine labyrinth gas seals structure in the tapered bleed hole of band |
| CN109505665A (en) * | 2018-12-26 | 2019-03-22 | 北京航空航天大学 | A kind of densification device based on aero-engine seal pan axial force negative feedback control |
| CN110726690A (en) * | 2019-10-11 | 2020-01-24 | 中国航发沈阳发动机研究所 | Multi-branch turbine disc cavity flow measurement structure and measurement method |
| CN112523813A (en) * | 2019-09-19 | 2021-03-19 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine rim sealing structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109296402A (en) * | 2017-07-25 | 2019-02-01 | 中国航发商用航空发动机有限责任公司 | Labyrinth gas seals structure and aero-engine |
-
2021
- 2021-03-26 CN CN202110323485.8A patent/CN113123879B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11315800A (en) * | 1998-04-30 | 1999-11-16 | Toshiba Corp | Air compressor |
| CN109139269A (en) * | 2017-06-27 | 2019-01-04 | 中国航发常州兰翔机械有限责任公司 | A kind of aero-engine labyrinth gas seals structure in the tapered bleed hole of band |
| CN109505665A (en) * | 2018-12-26 | 2019-03-22 | 北京航空航天大学 | A kind of densification device based on aero-engine seal pan axial force negative feedback control |
| CN112523813A (en) * | 2019-09-19 | 2021-03-19 | 中国航发商用航空发动机有限责任公司 | Aeroengine turbine rim sealing structure |
| CN110726690A (en) * | 2019-10-11 | 2020-01-24 | 中国航发沈阳发动机研究所 | Multi-branch turbine disc cavity flow measurement structure and measurement method |
Non-Patent Citations (2)
| Title |
|---|
| Effect of Linear Coupling Thermo-elasticity on Radial Clearance;Ding Shuiting，Li Ye，Zhang Gong;《PROCEEDINGS OF 2009 INTERNATIONAL SYMPOSIUM ON AIRCRAFT AIRWORTHINESS》;20091104;第382-387页 * |
| 航空发动机转子气体轴向力技术研究;王秋阳，陈亮;《中国设备工程》;20180410;第73-176页 * |
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| CN113123879A (en) | 2021-07-16 |
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