CN114837816A - Guide plate type vortex reducer with variable angle - Google Patents

Guide plate type vortex reducer with variable angle Download PDF

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Publication number
CN114837816A
CN114837816A CN202210610215.XA CN202210610215A CN114837816A CN 114837816 A CN114837816 A CN 114837816A CN 202210610215 A CN202210610215 A CN 202210610215A CN 114837816 A CN114837816 A CN 114837816A
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CN
China
Prior art keywords
servo motor
inlet
compressor
guide plate
angle
Prior art date
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Pending
Application number
CN202210610215.XA
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Chinese (zh)
Inventor
罗翔
何建
白阳
刘冬冬
邬泽宇
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Beihang University
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Beihang University
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Filing date
Publication date
Application filed by Beihang University filed Critical Beihang University
Priority to CN202210610215.XA priority Critical patent/CN114837816A/en
Publication of CN114837816A publication Critical patent/CN114837816A/en
Pending legal-status Critical Current

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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/70—Type of control algorithm
    • F05D2270/706—Type of control algorithm proportional-integral-differential
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention relates to a variable-angle guide plate type vortex reducer, which comprises: the air compressor comprises guide plates which are circumferentially and uniformly distributed in a disc cavity of the air compressor and angle adjusting devices which are respectively connected with the guide plates. The invention realizes the adjustment of the inlet angle of the guide plate by using the angle adjusting device and reduces the pressure loss at the inlet position.

Description

Guide plate type vortex reducer with variable angle
Technical Field
The invention relates to the technical field of cooling systems, in particular to a guide plate type vortex reducer with a variable angle.
Background
With the continuous development of the modern aviation industry, the aero-engine develops towards the direction of high thrust-weight ratio, high efficiency, high reliability and low oil consumption, the thrust-weight ratio can be effectively increased by increasing the temperature of the turbine inlet, and the oil consumption can be reduced by increasing the compression ratio of the gas compressor. Due to the limitations of turbine materials, the turbine front blade temperature must be cooled to a lower range. At present, the cooling of the hot end part of the existing aircraft engine is carried out through an air system, air is introduced from an air compressor drum hole by internal air introduction, flows into an axis channel through an air compressor disc cavity rotating at a high speed, and finally enters a turbine disc cavity. This radial bleed section is under a high centrifugal field and the presence of coriolis forces also creates a barrier to the radial inflow of gas due to the development of free vortices. After being led out from a proper position of the compressor, the cooling air passes through a designed flow channel and finally reaches a target position, and a series of pressure losses are generated in the bleed air channel. Therefore, a series of measures is required in design to reduce the pressure loss of the cold air as much as possible.
The vortex reducers which are widely applied at the present stage are tubular vortex reducers, reverse-rotation nozzle vortex reducers and fin vortex reducers. The installation of the vortex reducer between the disk cavities of the compressor can effectively limit the development of free vortex, thereby reducing the Cogowski force and the centrifugal force and reducing the pressure loss of gas. However, these vortex reducers have disadvantages, particularly in that significant pressure losses are created at the inlet locations of the air streams flowing through the vortex reducer structure, limiting the drag reducing effect of the vortex reducer.
Disclosure of Invention
In view of this, the present invention provides a variable angle baffle type vortex reducer to reduce pressure loss of gas at an inlet position by adjusting an inlet angle.
In order to achieve the purpose, the invention provides the following scheme:
a variable angle deflector-plate vortex reducer, the vortex reducer comprising: the air compressor comprises guide plates which are uniformly distributed in the circumferential direction in a disc cavity of the air compressor, and angle adjusting devices which are respectively connected with each guide plate, wherein the angle adjusting devices are used for adjusting the inlet angles of the guide plates; the inlet angle is an included angle between a plane where the inlet of the guide plate is located and a tangent line of a circumference where the center of the inlet of the guide plate is located.
Optionally, the angle adjusting device comprises a servo motor, a transmission shaft and a support shaft;
the servo motor is fixedly arranged on the inner side surface of an upstream compressor disk or a downstream compressor disk which is encircled into the compressor disk cavity, and one end of the corresponding support shaft is fixedly arranged on the inner side surface of the downstream compressor disk or the upstream compressor disk which is encircled into the compressor disk cavity;
one end of the transmission shaft is fixedly connected with an output shaft of the servo motor; the other end of the transmission shaft is fixedly connected with one side surface of the guide plate;
the other end of the supporting shaft is rotatably connected with the other side surface of the guide plate;
the supporting shaft, the transmission shaft and an output shaft of the servo motor are on the same axis, and the servo motor is used for driving the guide plate to rotate around the axis.
Optionally, the air deflector comprises a rotating part and a fixing part;
the angle adjusting device comprises a servo motor and a rotating shaft;
the servo motor is fixedly arranged on the inner side surface of an upstream compressor disk or a downstream compressor disk which is enclosed into the compressor disk cavity;
two side surfaces of the fixed part are respectively and fixedly connected with the inner side surfaces of an upstream compressor disk and a downstream compressor disk which enclose the compressor disk cavity;
the two ends of the rotating shaft are rotatably arranged on one side face, close to the rotating part, of the fixing part through a bearing, one side, close to the fixing part, of the rotating part is fixedly connected with the rotating shaft, and an output shaft of the servo motor is connected with one end of the rotating shaft.
Optionally, the vortex reducer further comprises a PID controller and a speed sensor disposed at an inlet of each baffle;
each speed sensor is connected with the PID controller; the PID controller is respectively connected with the control end of the driver of each servo motor;
the speed sensor is used for detecting the speed of the airflow flowing into the inlet of the deflector;
and the PID controller is used for controlling a servo motor at the inlet of each speed sensor to adjust the inlet angle of each guide plate by adopting a PID control algorithm according to the difference value between the air flow speed detected by each speed sensor and the actual rotating speed of the vortex reducer, so that all the difference values are smaller than a preset threshold value.
Optionally, the vortex reducer further comprises a wireless induction power supply system and a rectifier filter;
the wireless induction power supply system comprises an external power supply, a resistor, a triode and an inductor;
one end of the resistor and one end of the primary coil of the inductor are both connected with the anode of the external power supply;
the other end of the resistor is connected with the base electrode of the triode, and the other end of the primary coil of the inductor is connected with the collector electrode of the triode;
the emitting electrode of the triode is connected with the negative electrode of the external power supply;
the external power supply, the triode and the primary coil of the inductor form an oscillating circuit;
the oscillating circuit is arranged outside the disc cavity of the air compressor;
the secondary coil of the inductor and the rectifier filter are arranged inside the compressor disc cavity and rotate along with the compressor disc cavity, two ends of the secondary coil are connected with the input end of the rectifier filter, and the output end of the rectifier filter is respectively connected with the power input end of a driver of the servo motor, the power input end of the PID controller and the power input end of the speed sensor.
Optionally, the compressor disk cavity is surrounded by an upstream compressor disk and a downstream compressor disk which are coaxially arranged, and a drum which vertically extends along the outer edges of the upstream compressor disk and the upstream compressor disk.
Optionally, a plurality of drum holes are formed in the drum, and the plurality of drum holes are respectively arranged corresponding to the inlets of the plurality of flow deflectors.
Optionally, the drum aperture is an oblong aperture.
Optionally, the adjustment range of the inlet angle is 0 to 90 °.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention discloses a guide plate type vortex reducer with a variable angle, which comprises: the air compressor comprises guide plates which are circumferentially and uniformly distributed in a disc cavity of the air compressor and angle adjusting devices which are respectively connected with the guide plates. The invention realizes the adjustment of the inlet angle of the guide plate by using the angle adjusting device and reduces the pressure loss at the inlet position.
The vortex reducer of the present invention also includes a PID regulator to adaptively adjust the inlet angle of each baffle according to the airflow velocity at the inlet of each baffle.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive labor.
Fig. 1 is a schematic structural diagram of a variable-angle baffle-type vortex reducer provided in embodiment 1 of the present invention;
fig. 2 is a schematic structural diagram of a first embodiment of an angle adjustment device and a baffle according to embodiment 1 of the present invention;
fig. 3 is a schematic structural diagram of a second embodiment of an angle adjustment device and a baffle according to embodiment 1 of the present invention;
fig. 4 is a schematic structural diagram of a third embodiment of an angle adjustment device and a baffle according to embodiment 1 of the present invention;
description of reference numerals:
1. an upstream compressor disk; 2. a downstream compressor disk; 3. a baffle; 31. a rotating part; 32. a fixed part; 4. a drum; 41. a drum bore; 5. a servo motor; 6. a drive shaft; 7. a support shaft; 8. and rotating the shaft.
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.
The invention aims to provide a guide plate type vortex reducer with a variable angle, so that the pressure loss of gas at an inlet position is reduced by adjusting the inlet angle.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1
The embodiment 1 of the present invention provides a variable-angle guide plate type vortex reducer, as shown in fig. 1, the vortex reducer may be disposed in a compressor disk cavity of a secondary air system of an aircraft engine, and is located at a radial flow guide section of a compressor, the compressor disk cavity is a disk cavity formed by an upstream compressor disk 1 and a downstream compressor disk 2 which are correspondingly disposed on both sides, and a drum 4 which is vertically extended along outer edges of the upstream compressor disk 1 and the downstream compressor disk 2, the drum 4 is provided with a plurality of drum holes 41, each drum hole 41 is used for introducing an air flow, and the vortex reducer includes:
the air compressor comprises guide plates 3 which are uniformly distributed in the circumferential direction in a disc cavity of the air compressor, and angle adjusting devices which are respectively connected with each guide plate 3, wherein the angle adjusting devices are used for adjusting the inlet angles of the guide plates 3; the inlet angle is an included angle between a plane where the inlet of the guide plate 3 is located and a tangent line of a circumference where the center of the inlet of the guide plate 3 is located. Each guide plate 3 is coaxial with the upstream compressor disk 1 and the downstream compressor disk 2, the structure of each guide plate 3 is the same, the installation radius of each guide plate 3 is the same, and each guide plate 3 axially penetrates through the compressor disk cavity.
In the running state of the gas compressor, the plurality of guide plates 3 and the gas compressor disks on the two sides rotate coaxially, at the same speed and in the same direction, and the air flow flows through the plurality of drum holes 41 to enter the cavity of the gas compressor disk and then flows into the axial channel of the gas compressor through the plurality of guide plates 3.
For example, as shown in fig. 2, the baffle 3 as a whole can be adjusted in the inlet angle by adjusting the angle of the whole baffle 3. At this time, the angle adjusting device comprises a servo motor 5, a transmission shaft 6 and a support shaft 7; the servo motor 5 is fixedly arranged on the inner side surface of the upstream compressor disk 1 or the downstream compressor disk 2 which encloses the compressor disk cavity, and one end of the corresponding support shaft 7 is fixedly arranged on the inner side surface of the downstream compressor disk 2 or the upstream compressor disk 1 which encloses the compressor disk cavity; one end of the transmission shaft is fixedly connected with an output shaft of the servo motor 5; the other end of the transmission shaft is fixedly connected with one side surface of the guide plate 3; the other end of the supporting shaft 7 is rotatably connected with the other side surface of the guide plate 3; the support shaft 7, the transmission shaft and 6 are arranged on the same axis, and the output shaft of the servo motor 5 is arranged on the same axis, and the servo motor 5 is used for driving the guide plate 3 to rotate around the axis.
For example, as shown in fig. 3, the baffle 3 may be divided into a rotating part 31 and a fixed part 32, the rotating part 31 may rotate relative to the fixed part 32, and the adjustment of the inlet angle of the baffle 3 is realized by adjusting the rotating part 31. At this time, the angle adjusting device includes a servo motor 5, and the baffle 3 includes a rotating part 31 and a fixing part 32; two side surfaces of the fixing part 32 are respectively and fixedly connected with the inner side surfaces of an upstream compressor disk 1 and a downstream compressor disk 2 which enclose the compressor disk cavity; the rotating part 31 and the fixing part 32 are connected through a rotating shaft 8; the two ends of the rotating shaft 8 are rotatably arranged on one side surface of the fixing portion 32 close to the rotating portion 31 through a bearing, one side of the rotating portion 31 close to the fixing portion 32 is fixedly connected with the rotating shaft 8, and an output shaft of the servo motor 5 is connected with one end of the rotating shaft 8. In this case, as shown in fig. 4, another rotating portion may be provided at the outlet of the baffle 3 to adjust the angle of the outlet plane. The range that the included angle can be adjusted is 0-45 degrees formed by the outlet plane of the guide plate 3 and the tangent line of the circumference where the central point of the outlet of the guide plate 3 is located.
Exemplarily, the vortex reducer further comprises a PID controller and a speed sensor provided at the inlet of each baffle 3; each speed sensor is connected with the PID controller; the PID controller is respectively connected with the control end of the driver of each servo motor; the speed sensor is used for detecting the air flow speed flowing into the inlet of the deflector 3; the PID controller is configured to control the servo motor at the inlet of each speed sensor to adjust the inlet angle of each guide plate 3 by using a PID control algorithm according to the difference between the air flow speed detected by each speed sensor and the actual rotation speed of the vortex reducer, so that all the differences are smaller than a preset threshold, which may be set according to actual needs, and is not limited herein.
Exemplarily, the vortex reducer further comprises a wireless induction power supply system and a rectifier filter; the wireless induction power supply system comprises an external power supply, a resistor, a triode and an inductor; one end of the resistor and one end of the primary coil of the inductor are both connected with the anode of the external power supply; the other end of the resistor is connected with the base electrode of the triode, and the other end of the primary coil of the inductor is connected with the collector electrode of the triode; the emitting electrode of the triode is connected with the negative electrode of the external power supply; the external power supply, the triode and the primary coil of the inductor form an oscillating circuit; the oscillating circuit is arranged outside the compressor disc cavity, is independent of the compressor disc cavity and does not rotate along with the compressor disc cavity; the secondary coil of the inductor and the rectifier filter are arranged inside the compressor disc cavity and rotate along with the compressor disc cavity, two ends of the secondary coil are connected with the input end of the rectifier filter, and the output end of the rectifier filter is respectively connected with the power input end of a driver of the servo motor, the power input end of the PID controller and the power input end of the speed sensor.
Illustratively, each of the drum holes 41 is configured to enhance the circulation of the air flow at the drum hole 41, and the drum holes 41 are illustratively oblong holes.
Illustratively, the adjustment range of the inlet angle is 0 to 90 °.
Based on the above embodiment, the advantages of the present invention are as follows:
the invention fully considers the aerodynamic characteristics, avoids the pressure loss caused by separation when the airflow flows through the inlet section of the vortex reducer, increases the flow area of the airflow, inhibits the development of free vortex in the radial inflow disc cavity, reduces the dissipation of the airflow caused by turning and rapid change of the airflow channel, and reduces the pressure loss in the system.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.

Claims (9)

1. A variable angle deflector-plate vortex reducer, comprising: the air compressor comprises guide plates which are uniformly distributed in a disc cavity of an air compressor in the circumferential direction, and angle adjusting devices which are respectively connected with each guide plate, wherein the angle adjusting devices are used for adjusting the inlet angles of the guide plates; the inlet angle is an included angle between a plane where the inlet of the guide plate is located and a tangent line of a circumference where the center of the inlet of the guide plate is located.
2. The variable angle deflector-plate vortex reducer of claim 1, wherein the angle adjustment means comprises a servo motor, a drive shaft, and a support shaft;
the servo motor is fixedly arranged on the inner side surface of an upstream compressor disk or a downstream compressor disk which is encircled into the compressor disk cavity, and one end of the corresponding support shaft is fixedly arranged on the inner side surface of the downstream compressor disk or the upstream compressor disk which is encircled into the compressor disk cavity;
one end of the transmission shaft is fixedly connected with an output shaft of the servo motor; the other end of the transmission shaft is fixedly connected with one side surface of the guide plate;
the other end of the supporting shaft is rotatably connected with the other side surface of the guide plate;
the supporting shaft, the transmission shaft and an output shaft of the servo motor are on the same axis, and the servo motor is used for driving the guide plate to rotate around the axis.
3. The variable angle baffle-type vortex reducer of claim 1 wherein the baffle includes a rotating portion and a fixed portion, the angular adjustment device including a servo motor and a rotating shaft;
the servo motor is fixedly arranged on the inner side surface of an upstream compressor disk or a downstream compressor disk which is enclosed into the compressor disk cavity;
two side surfaces of the fixed part are respectively and fixedly connected with the inner side surfaces of an upstream compressor disk and a downstream compressor disk which enclose the compressor disk cavity;
the two ends of the rotating shaft are rotatably arranged on one side face, close to the rotating part, of the fixing part through bearings, one side, close to the fixing part, of the rotating part is fixedly connected with the rotating shaft, and an output shaft of the servo motor is connected with one end of the rotating shaft.
4. The variable angle baffle-type vortex reducer of claim 2 or 3, wherein the vortex reducer further comprises a PID controller and a velocity sensor disposed at an inlet of each baffle;
each speed sensor is connected with the PID controller; the PID controller is respectively connected with the control end of the driver of each servo motor;
the speed sensor is used for detecting the speed of the airflow flowing into the inlet of the deflector;
and the PID controller is used for controlling a servo motor at the inlet of each speed sensor to adjust the inlet angle of each guide plate by adopting a PID control algorithm according to the difference value between the air flow speed detected by each speed sensor and the actual rotating speed of the vortex reducer, so that all the difference values are smaller than a preset threshold value.
5. The variable angle deflector-plate vortex reducer of claim 4, further comprising a wireless induction power supply system and a rectifier filter;
the wireless induction power supply system comprises an external power supply, a resistor, a triode and an inductor;
one end of the resistor and one end of the primary coil of the inductor are both connected with the anode of the external power supply;
the other end of the resistor is connected with the base electrode of the triode, and the other end of the primary coil of the inductor is connected with the collector electrode of the triode;
the emitting electrode of the triode is connected with the negative electrode of the external power supply;
the external power supply, the triode and the primary coil of the inductor form an oscillating circuit;
the oscillating circuit is arranged outside the disc cavity of the air compressor;
the secondary coil of the inductor and the rectifier filter are arranged inside the compressor disc cavity and rotate along with the compressor disc cavity, two ends of the secondary coil are connected with the input end of the rectifier filter, and the output end of the rectifier filter is respectively connected with the power input end of a driver of the servo motor, the power input end of the PID controller and the power input end of the speed sensor.
6. The variable angle deflector-plate vortex reducer of claim 1, wherein the compressor disk cavity is enclosed by coaxially disposed upstream and downstream compressor disks and a vertically extending drum at outer edges of the upstream and downstream compressor disks.
7. The variable angle spoiler-type vortex reducer according to claim 6, wherein a plurality of drum holes are provided on said drum, and a plurality of said drum holes are respectively provided corresponding to inlets of said plurality of said deflectors.
8. The variable angle deflector plate vortex reducer of claim 7, wherein the drum bore is an oblong bore.
9. The variable angle baffle vortex reducer of claim 1 wherein the adjustment range of the inlet angle is 0 ° to 90 °.
CN202210610215.XA 2022-05-31 2022-05-31 Guide plate type vortex reducer with variable angle Pending CN114837816A (en)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120301272A1 (en) * 2011-05-26 2012-11-29 Rolls-Royce Plc Vortex reducer
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CN112377307A (en) * 2020-10-28 2021-02-19 北京航空航天大学 Curved tube type vortex reducing system with high-radius outlet
CN113652952A (en) * 2021-08-26 2021-11-16 深圳市鑫神科技开发有限公司 Vortex elimination method and vortex elimination device

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120301272A1 (en) * 2011-05-26 2012-11-29 Rolls-Royce Plc Vortex reducer
CN202833323U (en) * 2012-07-10 2013-03-27 重庆美的通用制冷设备有限公司 Centrifugal compressor guide vane regulating device
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
CN112377307A (en) * 2020-10-28 2021-02-19 北京航空航天大学 Curved tube type vortex reducing system with high-radius outlet
CN113652952A (en) * 2021-08-26 2021-11-16 深圳市鑫神科技开发有限公司 Vortex elimination method and vortex elimination device

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