CN114718910A - Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor - Google Patents
Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor Download PDFInfo
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- CN114718910A CN114718910A CN202110011674.1A CN202110011674A CN114718910A CN 114718910 A CN114718910 A CN 114718910A CN 202110011674 A CN202110011674 A CN 202110011674A CN 114718910 A CN114718910 A CN 114718910A
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- vortex
- movable section
- air
- vortex reducing
- reducer
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 24
- 239000013598 vector Substances 0.000 title claims abstract description 12
- 238000000034 method Methods 0.000 title claims abstract description 7
- 230000003044 adaptive effect Effects 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 230000009467 reduction Effects 0.000 description 8
- 238000001816 cooling Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000740 bleeding effect Effects 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a self-adaptive vector vortex reducer, a high-pressure compressor and an air entraining method of the high-pressure compressor, wherein the self-adaptive vector vortex reducer comprises a vortex reducing pipe and comprises a fixed section and a movable section, the fixed section and the movable section can adapt to complex flow conditions, the movable section is provided with an air inlet of the vortex reducing pipe, the fixed section and the movable section can be movably connected, and the movable section is integrally arranged into a pneumatic structure which can be driven by air entraining.
Description
Technical Field
The invention relates to a bleed air device of an aircraft engine, in particular to a vortex reducer.
Background
With the development of the technology of the aero-engine, the temperature in front of the turbine is increased to effectively improve the efficiency of the engine, but higher requirements are provided for cooling the turbine blades, on one hand, turbine cooling gas is mainly introduced by the main flow of the high-pressure compressor, the introduced gas flow does not participate in the work of the compressor, and the important influence is exerted on the oil consumption rate. Therefore, improving the utilization rate of bleed air and taking measures to reduce the pressure loss of the bleed air along the way are very critical in the design of the engine.
At present, the mainstream aircraft engine mainly introduces air from the inner side of the mainstream of the high-pressure compressor, the air flow flows in through a disk cavity of the compressor along the radial direction, and then flows into a turbine disk cavity through a channel between disk shafts of the high-pressure compressor, and then cools turbine blades. The airflow flows through the rotating disc cavity, and under the high-speed driving of the disc cavity, the airflow can have strong vortex, so that the great pressure loss is caused. In order to reduce the loss of bleed air flow in a disc cavity, a tubular vortex reducer is widely applied to conventional vortex reducers at present, but the flow condition is relatively complex because the vortex state in the disc cavity changes along with the change of the rotating speed of a gas compressor, and meanwhile, the radial inner flow is influenced by the action of inertia force, centrifugal force and coriolis force, the reduction effect of the pressure loss when the air flow flows into the vortex reducer is very limited by the orientation and the size of a fixed opening of the conventional vortex reducer, and the complicated flow in the disc cavity is difficult to adapt.
Disclosure of Invention
It is an object of the present invention to provide a vortex reducing tube which can accommodate complex flow conditions.
It is another object of the present invention to provide an adaptive deswirler that further reduces pressure loss and increases cooling efficiency.
It is a further object of the present invention to provide a compressor that reduces pressure loss caused by bleed air.
Still another object of the present invention is to provide a method of bleeding air for a compressor, which can reduce pressure loss caused by the bleed air.
The vortex reducing pipe comprises a fixed section and a movable section, wherein the movable section is provided with an air inlet of the vortex reducing pipe, the fixed section is movably connected with the movable section, and the movable section is integrally arranged into a pneumatic structure driven by air entraining.
In one embodiment, the movable section is arranged to rotate about its axis, the air inlet being at an angle to the axis.
In one embodiment, the movable section and the fixed section are connected by a bearing.
In one embodiment, the bearing is a ball bearing.
In one embodiment, the air inlet is defined by a cut-out of the active segment.
In one embodiment, the fixed segment and the movable segment are disposed coaxially or intersect.
In one embodiment, a baffle is disposed on an outer peripheral side of the movable section.
The self-adaptive vector vortex reducer further comprises a support ring, wherein a plurality of vortex reducing pipes are uniformly distributed on the support ring, and the vortex reducing pipes are any vortex reducing pipe.
In an embodiment, the fixing segments are arranged to extend in a radial direction of the support ring.
A high-pressure compressor comprises a drum barrel, a wheel disc and a vortex reducer, wherein an air guide hole is formed in the drum barrel, the vortex reducer is installed on the wheel disc, the vortex reducer is an adaptive vector vortex reducer, and an air inlet and the air guide hole are arranged oppositely.
The air entraining method of the high-pressure compressor is characterized in that an air inlet of the vortex reducing pipe is arranged on a movable section, and the movable section is arranged into a pneumatic structure which can be driven by the air entraining airflow; the movable section is driven by the air-entraining airflow, and the air inlet is guided to move towards a position vertical to the incoming flow direction along with the incoming flow direction by the movement of the movable section.
According to the technical scheme, the movable section is added, the vortex reducing pipe is adapted to vectors in different vortex states, the air entraining flow is increased, the pressure loss is reduced, and the air entraining efficiency and the cooling efficiency are increased.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of an internal cavity bleed air structure of an aircraft engine.
Fig. 2 is a schematic cross-sectional view of a vertical vortex reducer.
Fig. 3 is a schematic view of a vertical vortex reducing pipe.
FIG. 4 is a schematic view of one state of a vortex reducing tube according to the present invention.
FIG. 5 is a schematic view of another state of a vortex reducing tube according to the present invention.
FIG. 6 is a schematic cross-sectional view of an adaptive swirl reducer.
Fig. 7 is a schematic view of a ball bearing.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
It is noted that these and other figures follow, given by way of example only, and are not drawn to scale, and should not be construed to limit the scope of the invention as it may be claimed.
Fig. 1 shows a schematic diagram of a conventional internal cavity bleed air structure of an aircraft engine, and fig. 2 shows a sectional view of a vertical vortex reducer. As shown in fig. 1, a plurality of compressor rotor blades 1 are axially installed on a disk 3, the disk 3 is connected to the disk 3 by a drum 2, and a vortex reducing pipe 4 is supported by a support structure on the inner peripheral side of the disk 3. High-pressure gas formed by the working of the blades 1 in the high-pressure compressor flows into a compressor disk cavity through the air guide holes 6 formed in the drum 2 and then sequentially flows into the vortex reducing pipe 4 and a turbine disk cavity which is not shown in the figure so as to cool the turbine blades. Under the high speed of the disk 3, there is a strong vortex in the air flow. The flow conditions are more complex as the swirl of the air flow varies with the rotational speed of the disc chamber 3. The standing vortex reducer includes a support ring 41 and a plurality of standing vortex reducing pipes 4 installed along a circumferential direction of the support ring 41.
As shown in fig. 3, the designed flow area of the vertical vortex reducing pipe 100 is a1, and the actual equivalent flow area is a2, the fixed opening orientation and size of the vertical vortex reducing pipe 100 is difficult to adapt to the complex flow in the disk cavity, so a2 is usually smaller than a 1.
As shown in fig. 4, the adaptive vector vortex reducing pipe comprises an upper vortex reducing pipe 7 and a lower vortex reducing pipe 9. The upper and lower vortex reducing pipes 7 and 9 correspond to the active and fixed sections of the adaptive vector vortex reducing pipe, respectively, the upper vortex reducing pipe 7 having an inlet 73 defined by a tangential plane 72. The lower vortex reduction tubes 9 are fixedly disposed relative to the engine drum, and specifically, as shown in fig. 6, a plurality of lower vortex reduction tubes 9 are fixed to a support ring 91, and the support ring 91 is fixed in the mounting position of the vortex reduction tube 4 shown in fig. 1. The upper vortex reducing pipe 7 is movably arranged relative to the lower vortex reducing pipe 9, and one of the movable arrangement modes is that the upper vortex reducing pipe and the lower vortex reducing pipe are connected through a ball bearing 8. As shown in fig. 7, the ball bearing 8 has an inner race 81, an outer race 82, and balls 83 provided between the inner race 81 and the outer race 82. In one embodiment, the ball bearing 8 is a separate member, one of the upper and lower vortex reducing pipes 7 and 9 is fixedly connected to the inner ring 81, and the other is fixedly connected to the outer ring 82, and the flow path wall surface at the connection is preferably made smooth. In another embodiment, the inner race 81 and the outer race 82 of the ball bearing 8 are provided by one and the other of the upper and lower vortex reducing tubes 7 and 9, respectively. The upper vortex reducing pipe 7 is supported by a ball bearing 8 and is arranged to rotate around the axis of the upper vortex reducing pipe 7, and the air inlet 73 and the axis of the upper vortex reducing pipe 7 form an included angle. The upper vortex reducing pipe 7 intersects with the axis of the lower vortex reducing pipe 9 or is arranged obliquely. In another embodiment, the upper vortex reduction duct 7 is arranged coaxially with the lower vortex reduction duct 9.
A baffle 71 is provided on the outer peripheral side of the upper vortex reduction duct 7, thereby making the upper vortex reduction duct 7 as a whole an aerodynamic structure that can be driven by bleed air. In operation, on the one hand, the flow passage environment around the vortex reducing pipe is relatively complex, and the direction and magnitude of the velocity of the incident airflow 10 at the upper vortex reducing pipe 7 port will change with the operating state (rotational speed) of the engine. Under the action of the incident airflow 10, the guide plates 71 mounted on the upper vortex reducing pipe 7 can drive the lower end of the upper vortex reducing pipe 7 to rotate under the support of the ball bearing 8 so as to face the direction of the incident airflow 10, fig. 4 and 5 show that the direction of the vortex reducing pipe is adaptively changed when the incident direction is different, the air inlet is guided to move towards the position vertical to the incoming flow direction along with the incident airflow 10 through the movement of the upper vortex reducing pipe 7, the air-entraining circulation is increased, and the problem that the equivalent flow area is reduced when the incident airflow obliquely irradiates the traditional vertical vortex reducing pipe shown in fig. 3 is solved. On the other hand, the problem that a large vortex is generated in the traditional vertical type vortex reducing pipe shown in the figure 3 is solved, and the pressure loss is reduced. The air-entraining efficiency and the cooling efficiency are increased.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. For example, the ball bearing 8 may be replaced by other rotational support means, such as a spherical plain bearing. As with the ball bearing 8, in fig. 4, the mounting is inclined and in another embodiment horizontal.
Through the foregoing embodiments, a method for bleeding air in a high-pressure compressor can be further understood, in which air is bled from an inner side of a main flow of the high-pressure compressor, the air flow flows in through a disk cavity of the compressor in a radial direction, a flow loss of the bleed air flow in the disk cavity is reduced through a vortex reducing pipe, an air inlet of the vortex reducing pipe is disposed on a movable section, the movable section is disposed in a pneumatic structure which can be driven by the bleed air flow, the movable section is driven by the bleed air flow, and the air inlet is guided to follow an incoming flow direction through the movement of the movable section and moves towards a position perpendicular to the incoming flow direction. At subtracting vortex pipe entrance, can be according to the condition automatically regulated mouth of pipe direction of incoming flow to guarantee the biggest bleed flow and reduce pressure loss.
Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (11)
1. The vortex reducing pipe is characterized by comprising a fixed section and a movable section, wherein the movable section is provided with an air inlet of the vortex reducing pipe, the fixed section is movably connected with the movable section, and the overall shape of the movable section is set into a pneumatic structure driven by air entraining.
2. The vortex reducing tube according to claim 1 wherein said movable section is arranged to rotate about its axis, said inlet being at an angle to said axis.
3. The vortex reducing tube according to claim 1 or 2, wherein said movable section and said fixed section are connected by a bearing.
4. The vortex reducing tube of claim 3 wherein said bearing is a ball bearing.
5. The vortex reducing tube according to claim 1 or 2, wherein said air inlet is defined by a cut surface of said movable section.
6. The vortex reducing tube according to claim 2, wherein said fixed section and said movable section are disposed coaxially or intersecting.
7. The vortex reducing tube according to claim 1, wherein a baffle is provided on an outer peripheral side of said movable section.
8. An adaptive vector vortex reducer, further comprising a support ring on which a plurality of vortex reducing pipes are uniformly distributed, wherein the vortex reducing pipes are vortex reducing pipes according to any one of claims 1 to 7.
9. The adaptive vector vortex reducer of claim 8, wherein the fixed segment is disposed to extend radially of the support ring.
10. A high-pressure compressor, comprising a drum, a wheel disc and a vortex reducer, wherein the drum is provided with an air-bleed hole, and the wheel disc is provided with the vortex reducer, characterized in that the vortex reducer is the adaptive vector vortex reducer according to claim 8 or 9, and the air inlet is arranged opposite to the air-bleed hole.
11. The air entraining method of the high-pressure compressor is characterized in that an air inlet of the vortex reducing pipe is arranged on a movable section, and the movable section is arranged into a pneumatic structure which can be driven by the air entraining airflow; the movable section is driven by the air-entraining airflow, and the air inlet is guided to move towards a position vertical to the incoming flow direction along with the incoming flow direction by the movement of the movable section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110011674.1A CN114718910A (en) | 2021-01-06 | 2021-01-06 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110011674.1A CN114718910A (en) | 2021-01-06 | 2021-01-06 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
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| Publication Number | Publication Date |
|---|---|
| CN114718910A true CN114718910A (en) | 2022-07-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110011674.1A Pending CN114718910A (en) | 2021-01-06 | 2021-01-06 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030101730A1 (en) * | 2001-12-05 | 2003-06-05 | Stefan Hein | Vortex reducer in the high-pressure compressor of a gas turbine |
| US20090282834A1 (en) * | 2008-05-19 | 2009-11-19 | Stefan Hein | Combined Vortex reducer |
| CN202789728U (en) * | 2012-09-28 | 2013-03-13 | 中航商用航空发动机有限责任公司 | Vortex reduction device of compressor and compressor |
| CN103867235A (en) * | 2012-12-18 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Tubular vortex reducer air inducing system |
| CN203685310U (en) * | 2013-12-11 | 2014-07-02 | 中航商用航空发动机有限责任公司 | Air entraining structure of eddy reduction device |
| CN204553354U (en) * | 2015-03-11 | 2015-08-12 | 中航商用航空发动机有限责任公司 | Subtract the gas compressor of scroll and aeroengine |
-
2021
- 2021-01-06 CN CN202110011674.1A patent/CN114718910A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030101730A1 (en) * | 2001-12-05 | 2003-06-05 | Stefan Hein | Vortex reducer in the high-pressure compressor of a gas turbine |
| US20090282834A1 (en) * | 2008-05-19 | 2009-11-19 | Stefan Hein | Combined Vortex reducer |
| CN202789728U (en) * | 2012-09-28 | 2013-03-13 | 中航商用航空发动机有限责任公司 | Vortex reduction device of compressor and compressor |
| CN103867235A (en) * | 2012-12-18 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Tubular vortex reducer air inducing system |
| CN203685310U (en) * | 2013-12-11 | 2014-07-02 | 中航商用航空发动机有限责任公司 | Air entraining structure of eddy reduction device |
| CN204553354U (en) * | 2015-03-11 | 2015-08-12 | 中航商用航空发动机有限责任公司 | Subtract the gas compressor of scroll and aeroengine |
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