CN113090593A - Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine - Google Patents
Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine Download PDFInfo
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- CN113090593A CN113090593A CN202110527645.0A CN202110527645A CN113090593A CN 113090593 A CN113090593 A CN 113090593A CN 202110527645 A CN202110527645 A CN 202110527645A CN 113090593 A CN113090593 A CN 113090593A
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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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Abstract
The invention discloses a reverse-rotation blade type vortex reducing and air entraining structure suitable for a turboshaft engine, which comprises an axial-flow compressor disk and a centrifugal impeller disk, wherein reverse-rotation blade vortex reducers are arranged on the inner sides of the axial-flow compressor disk and the centrifugal impeller disk and are connected to the centrifugal impeller disk through screws, a circle of non-throttling air entraining grooves are formed between the axial-flow compressor disk and the centrifugal impeller disk along the circumferential direction, blade type air entraining channels matched with the air entraining grooves are formed on the reverse-rotation blade vortex reducers along the circumferential direction, a supporting plate is arranged at the bottom of the reverse-rotation blade vortex reducers, and the other end of the supporting plate is coupled on the inner side of the centrifugal impeller disk. The weight reduction was about 50%.
Description
Technical Field
The invention belongs to the technical field of a turboshaft engine, and particularly relates to a reverse-vane type vortex-reducing air-entraining structure suitable for the turboshaft engine.
Background
In the design of a medium-small aircraft engine, a compact structure design is often adopted for reducing the cost, and meanwhile, because the radius of the engine is lower, the air is introduced from the root of a final-stage axial flow compressor to have proper pressure and temperature, and a vortex reducing measure or an air introducing disc type vortex reducing structure is generally not adopted.
The conventional axial flow compressor bleed air structure is shown in fig. 1, that is, fig. 1 is a bleed air structure without a vortex reducer, and bleed air of an air system radially and inwards passes through a disk cavity with rotating wall surfaces on two sides and then enters downstream parts for cooling.
The common bleed air plate vortex reducer bleed structure of the aviation type turboshaft engine is shown in fig. 2 and fig. 3, cold air is led from a main flow channel and enters the bleed air plate vortex reducer through a bleed air hole, the bleed air plate vortex reducer is connected with a compressor turntable, and the cold air is used for cooling downstream parts after passing through the vortex reducer.
The air entraining design of the air compressor without the vortex reducing structure has the advantages that the air flow is driven to rotate by the air compressor turntable, the turntable applies work to the air flow through friction, the air flow generates a large circumferential speed, and meanwhile, the air flow rotates in an accelerating manner under the action of radial internal flow Coriolis force, and a large pressure drop is generated along the radial direction.
The bleed disc deswirler bleed air velocity triangle is shown in fig. 4.
Subscript 0: main flow parameters close to the inlet section of the vortex reducing pipe;
subscript 1: representing a reduced vortex tube inlet cross-sectional parameter;
subscript 2: representing a vortex reducing pipe outlet section parameter;
(C: absolute velocity; U: rotational coordinate system involvement velocity; W: relative velocity)
The bleed disc type vortex reducer rotates along with the compressor disc, so that the relative speed W in the vortex reducing pipe is vertical downward, the main flow bleed air W0 enters the inlet W1 of the vortex reducing pipe, the airflow turns sharply, large pressure loss exists locally, and according to a vector synthesis law, the tangential component of the absolute speed C of the airflow in the bleed disc type vortex reducer is large, namely, the tangential component is high in swirl coefficient, and large radial pressure drop is caused.
Disclosure of Invention
The invention aims to provide a reverse-vane type vortex-reducing air-entraining structure suitable for a turboshaft engine so as to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
the anti-rotation blade type vortex reducing air entraining structure suitable for the turboshaft engine comprises an axial flow compressor disk and a centrifugal impeller disk, wherein an anti-rotation blade vortex reducer is arranged on the inner sides of the axial flow compressor disk and the centrifugal impeller disk, the anti-rotation blade vortex reducer is connected to the centrifugal impeller disk through screws, a circle of non-throttling air entraining groove is formed between the axial flow compressor disk and the centrifugal impeller disk along the circumferential direction, and a blade type air entraining channel matched with the air entraining groove is formed in the anti-rotation blade vortex reducer along the circumferential direction.
As a still further scheme of the invention: the deswirler of the reverse-rotation blade is fixedly connected with the centrifugal impeller disc through two screws, and the two screws are symmetrically arranged on the centrifugal impeller disc along the circumferential direction.
As a still further scheme of the invention: the bottom of the deswirler of the counter-rotating blade is provided with a supporting plate, and the other end of the supporting plate is coupled to the inner side of the centrifugal impeller disc.
As a still further scheme of the invention: the axial flow compressor disk and the centrifugal impeller disk are connected through splines to transmit torque, and a gap of a hollow groove between the axial flow compressor disk and the centrifugal impeller disk is 0.5 mm.
As a still further scheme of the invention: and a semicircle with the diameter of 5mm is circumferentially arranged on the groove surface where the centrifugal impeller disc is connected with the axial flow compressor disc.
As a still further scheme of the invention: the vortex reducing device with the counter-rotating blades is provided with a plurality of blades in an annular array, and the inlet blade angle of the vortex reducing device with the counter-rotating blades is consistent with the relative airflow angle WO of the inlet of the main flow air introduced through the air guide grooves.
As a still further scheme of the invention: the outlet blade angle of the counter-rotating blade vortex reducer and the tangent line of the inscribed circle form an included angle of 35 degrees, and the direction is opposite to the rotating direction of the centrifugal impeller disc.
As a still further scheme of the invention: the number of the blades of the deswirler is 12, and the axial length of the inner flow passage of the deswirler is 6-13 mm.
Compared with the prior art, the invention has the beneficial effects that:
1. the anti-rotation blade vortex reducer is integrally cast, the structure is simple and light, the weight of the area of the vortex reducing channel is greatly reduced due to the adoption of the annular cascade flow guiding form in the vortex reducing channel, and compared with an air-entraining disc type vortex reducer with the same size, the weight is reduced by about 50%;
2. compared with the air entraining disk type vortex reducer, the vane type vortex reducing air entraining structure increases the static pressure coefficient (local static pressure/inlet static pressure) of an air entraining outlet from 0.7 to 0.85-0.9, better ensures the air supply pressure of a downstream element of a cooling flow path, and the vortex reducer with the axial length of 6mm increases the work of air entraining airflow by 30 percent, reduces the outlet rotational flow coefficient to 0.2, adopts the scheme with the axial length of 12mm, and has the static pressure coefficient of the air entraining outlet of 0.9.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
Fig. 1 is a schematic structural diagram of a prior art non-vortex-reducing bleed air structure.
Fig. 2 is a structural schematic diagram of a bleed structure of a bleed disc vortex reducer in the prior art.
Fig. 3 is a structural schematic diagram of a three-dimensional structural section of a bleed disc vortex reducer in the prior art.
Fig. 4 is a schematic structural diagram of a speed triangle of an inlet and an outlet of a bleed disc vortex reducer in the prior art.
FIG. 5 is a schematic structural diagram of a two-position cross-sectional view of a deswirler with counter-rotating blades according to the present invention.
FIG. 6 is a schematic view of the structure of the gas introduction groove of the present invention.
FIG. 7 is a sectional view of a deswirler with counter-rotating blades and a structural schematic diagram of inlet and outlet velocity triangles according to the present invention.
FIG. 8 is a schematic view of the structure defined by the exit blade angle of the deswirler vane of the present invention.
FIG. 9 is a schematic view of the axial length of the flow passage in the deswirler with counter-rotating blades according to the present invention.
FIG. 10 is a schematic structural view of the static pressure coefficient of the air induction disk deswirler of the present invention.
FIG. 11 is a schematic structural view of the swirl coefficient of the air induction plate vortex reducer of the present invention.
FIG. 12 is a schematic structural view showing the static pressure coefficient distribution in the present invention (12 vanes, outlet vane angle 35 degrees, axial length 6 mm).
FIG. 13 is a structural diagram showing the distribution of swirl coefficients in the present invention (12 vanes, outlet vane angle 35 degrees, axial length 6 mm).
FIG. 14 is a schematic structural view showing the static pressure coefficient distribution in the present invention (12 vanes, outlet vane angle 35 degrees, axial length 9 mm).
FIG. 15 is a structural schematic diagram of the velocity vector distribution of the present invention (12 vanes, exit vane angle 35, axial length 9 mm).
In the figure: 1. an axial flow compressor disk; 2. a centrifugal impeller disc; 3. a counter-rotating blade deswirler; 4. a screw; 5. an air introducing groove; 6. a bleed air passage; 7. and a support plate.
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 a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 5-6, in the embodiment of the present invention, the anti-rotation blade type vortex reducing and air entraining structure suitable for a turbo shaft engine includes an axial flow compressor disk 1 and a centrifugal impeller disk 2, the inner sides of the axial flow compressor disk 1 and the centrifugal impeller disk 2 are provided with an anti-rotation blade vortex reducer 3, the anti-rotation blade vortex reducer 3 is connected to the centrifugal impeller disk 2 through a screw 4, the axial flow compressor disk 1 and the centrifugal impeller disk 2 are connected by a spline to transmit a torque, a circle of unthrottled air entraining grooves 5 are formed between the two disks along a circumferential direction, and the anti-rotation blade vortex reducer 3 is provided with an air entraining channel 6 adapted to the air entraining grooves 5 along the circumferential direction.
When the vortex reducing device is used, the counter-rotating blade vortex reducing device 3 is integrally cast, the structure is simple and light, and the weight of the partial region of the vortex reducing channel is greatly reduced due to the adoption of the annular cascade flow guiding form in the vortex reducing channel;
the counter-rotating blade vortex reducer 3 is of a disc structure with a narrow top and a wide bottom, stress is uniformly distributed when the counter-rotating blade vortex reducer 3 rotates along the circumferential direction, and the strength life of parts is guaranteed to meet requirements.
Referring to fig. 5, the deswirler 3 is fastened to the centrifugal impeller disk 2 by two screws 4, and the two screws 4 are symmetrically arranged on the centrifugal impeller disk 2 along the circumferential direction.
The connection of the deswirler 3 and the centrifugal impeller disk 2 is more secure.
Referring to fig. 5, the bottom of the deswirler 3 is provided with a support plate 7, and the other end of the support plate 7 is coupled to the inside of the centrifugal impeller disk 2.
When the vortex reducer is used, the supporting plate 7 is arranged, namely the supporting plate 7 is fixed on the inner diameter of the centrifugal impeller disc 2, and the vortex reducer 3 for the counter-rotating blades is supported and damped.
Referring to fig. 7-8, torque is transmitted between the axial flow compressor disk 1 and the centrifugal impeller disk 2 through splines, a slot gap between the axial flow compressor disk 1 and the centrifugal impeller disk 2 is 0.5mm, a semicircle with a diameter of 5mm is circumferentially arranged on a slot surface where the centrifugal impeller disk 2 is connected with the axial flow compressor disk 1, the anti-rotation vane vortex reducer 3 is provided with a plurality of vanes in an annular array, an inlet vane angle of the anti-rotation vane vortex reducer 3 is consistent with an inlet relative airflow angle WO of mainstream air introduced through the air-entraining slot 5, so as to guide inlet airflow to reduce pressure loss of cold air at the front end of an inlet of the anti-rotation vane vortex reducer 3, an outlet vane angle of the anti-rotation vane vortex reducer 3 forms an included angle of 35 degrees with an inscribed circle tangent line, the direction is opposite to the rotation direction of the centrifugal impeller disk 2, airflow expansion capacity and air-entraining speed in a rotary contraction rotational flow passage are controlled, and airflow at an outlet has higher pressure and low rotational flow coefficient, the power loss of an engine can be reduced, the loss of a cold air inflow port is reduced, the radial pressure drop of airflow is inhibited, the static pressure of an outlet is improved, the rotational flow coefficient and the temperature of the outlet are reduced, and the quality of air flow of air entraining is improved.
Referring to fig. 9-15, the number of the blades of the deswirler 3 is 12, and the axial length of the flow passage in the deswirler 3 is 6-13 mm.
When the three-dimensional CFD vortex reducer is used, through three-dimensional CFD calculation and evaluation, the calculation result shows that when the number of the blades is 12, the inlet angle is consistent with the angle of the main stream bleed air relative speed W0, a better vortex removing effect can be achieved when the angle of the outlet blade of the reverse-rotation blade vortex reducer forms an included angle of 35 degrees with the axial direction, and the volume (weight) of the reverse-rotation blade vortex reducer is reduced by about 50 percent compared with that of the bleed air disc vortex reducer.
According to the scheme that the axial length of the counter-rotating blade vortex reducer is 6mm, the output power of cold air flow is increased by about 30% compared with that of the air guide plate vortex reducer, the temperature is reduced by about 5 ℃, and the static pressure coefficient and the rotational flow coefficient of an outlet are 0.85 and 0.2 respectively.
The axial length of the counter-rotating blade vortex reducer is 9mm, the static pressure coefficient of an outlet of the counter-rotating blade vortex reducer can reach 0.9, a separation low-pressure area is formed at the position of a blade basin in a channel due to the increase of the flow area of a throat, the transverse pressure difference of the channel is restrained, the airflow is in a critical state of acting and being acted, and the temperature of the airflow does not drop when the airflow passes through the counter-rotating blade vortex reducer.
The counter-rotating blade type vortex reducer of the invention has advantages in weight and air-entraining quality compared with the air-entraining disk vortex reducer, as shown in the following table
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.
Claims (8)
1. A counter-rotating blade type vortex reducing and air entraining structure applicable to a turboshaft engine is characterized by comprising an axial flow compressor disk (1) and a centrifugal impeller disk (2), wherein a counter-rotating blade vortex reducer (3) is arranged on the inner sides of the axial flow compressor disk (1) and the centrifugal impeller disk (2), the counter-rotating blade vortex reducer (3) is connected to the centrifugal impeller disk (2) through a screw (4), the axial flow compressor disk (1) and the centrifugal impeller disk (2) are connected through splines, a round non-throttling air entraining groove (5) is formed in the circumferential direction, and a blade type air entraining channel (6) matched with the air entraining groove (5) is formed in the counter-rotating blade vortex reducer (3) in the circumferential direction.
2. The anti-rotation blade type vortex reducing and air entraining structure applicable to the turboshaft engine according to claim 1, characterized in that the anti-rotation blade vortex reducer (3) is tightly connected with the centrifugal impeller disk (2) through two screws (4), and the two screws (4) are symmetrically arranged on the centrifugal impeller disk (2) along the circumferential direction.
3. The anti-rotary vane type vortex reducing and air entraining structure suitable for the turboshaft engine according to claim 1, characterized in that the bottom of the anti-rotary vane vortex reducer (3) is provided with a support plate (7), and the other end of the support plate (7) is coupled inside the centrifugal impeller disk (2).
4. The anti-vane type vortex reducing and air entraining structure suitable for the turboshaft engine according to claim 1, characterized in that the empty slot gap between the axial compressor disk (1) and the centrifugal impeller disk (2) is 0.5 mm.
5. The anti-rotation blade type vortex reducing and air entraining structure suitable for the turboshaft engine according to claim 4, wherein a semi-circle with a diameter of 5mm is circumferentially arranged on a groove surface of the centrifugal impeller disk (2) connected with the axial flow compressor disk (1).
6. The anti-swirl vane vortex reducing bleed air structure for a turboshaft engine according to claim 1, characterized in that the anti-swirl vane vortex reducer (3) is provided with a plurality of vanes in an annular array, and the inlet vane angle of the anti-swirl vane vortex reducer (3) is consistent with the inlet relative flow angle WO of the main flow air introduced through the bleed air groove (5).
7. The anti-rotation blade type vortex reducing and air entraining structure suitable for the turboshaft engine according to claim 6, characterized in that the outlet blade angle of the anti-rotation blade vortex reducer (3) is at an angle of 35 ° with the tangent of the inscribed circle, and the direction is opposite to the rotation direction of the centrifugal impeller disk (2).
8. The anti-rotation blade type vortex reducing and air entraining structure applicable to the turboshaft engine according to claim 6, characterized in that the number of blades of the anti-rotation blade vortex reducer (3) is 12, and the axial length of the flow passage in the anti-rotation blade vortex reducer (3) is 6-13 mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110527645.0A CN113090593A (en) | 2021-05-14 | 2021-05-14 | Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110527645.0A CN113090593A (en) | 2021-05-14 | 2021-05-14 | Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine |
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| CN113090593A true CN113090593A (en) | 2021-07-09 |
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| CN202110527645.0A Pending CN113090593A (en) | 2021-05-14 | 2021-05-14 | Anti-rotation blade type vortex reduction air entraining structure suitable for turboshaft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114838006A (en) * | 2022-04-29 | 2022-08-02 | 北京航空航天大学 | Baffle type vortex-reducing air-entraining system for compressor |
Citations (5)
| 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 |
| US20050172640A1 (en) * | 2004-02-11 | 2005-08-11 | Steffen Drevs | Tube-type vortex reducer |
| CN203614465U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Baffle mode eddy device of gas compressor and gas compressor |
| CN110454436A (en) * | 2019-07-29 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed |
| CN112377308A (en) * | 2020-10-28 | 2021-02-19 | 北京航空航天大学 | Anti-rotation fin type vortex reduction system with high-radius outlet |
-
2021
- 2021-05-14 CN CN202110527645.0A patent/CN113090593A/en active Pending
Patent Citations (5)
| 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 |
| US20050172640A1 (en) * | 2004-02-11 | 2005-08-11 | Steffen Drevs | Tube-type vortex reducer |
| CN203614465U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Baffle mode eddy device of gas compressor and gas compressor |
| CN110454436A (en) * | 2019-07-29 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed |
| CN112377308A (en) * | 2020-10-28 | 2021-02-19 | 北京航空航天大学 | Anti-rotation fin type vortex reduction system with high-radius outlet |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114838006A (en) * | 2022-04-29 | 2022-08-02 | 北京航空航天大学 | Baffle type vortex-reducing air-entraining system for compressor |
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