CN108105164A - A kind of axial thrust balancing devices - Google Patents
A kind of axial thrust balancing devices Download PDFInfo
- Publication number
- CN108105164A CN108105164A CN201711341208.XA CN201711341208A CN108105164A CN 108105164 A CN108105164 A CN 108105164A CN 201711341208 A CN201711341208 A CN 201711341208A CN 108105164 A CN108105164 A CN 108105164A
- Authority
- CN
- China
- Prior art keywords
- balancing frame
- balancing
- comb tooth
- axial thrust
- frame
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- F04D29/662—Balancing of rotors
Abstract
The present invention provides a kind of axial thrust balancing devices, the device is tested applied to birotor, at rotor portion rear, balancing frame (4) is set, balancing frame (4) outer diameter sets a circle comb tooth row, by touching connection component to be connected with casing wall surface on the outside of comb tooth row, and then balancing frame (4) both sides form former and later two cavity volumes, it is circumferentially opened up on cavity volume casing wall surface before balancing frame (4) and builds pressure hole (2), cavity volume before the high pressure gas introducing balancing frame (4) in exhaust duct (1) is formed high pressure chest (3), cavity volume leads to air to form low pressure chamber (5) to balancing frame (4) afterwards, front and rear differential pressure action is on balancing frame (4), offset axial force.Axial thrust balancing devices provided by the present invention, balancing frame balancing device are by the structure design in the range of Compressor test part, and axial force balance is realized inside compressor, are decoupled with external equipment, are more advantageous to the independent debugging of equipment.
Description
Technical field
The invention belongs to Aeroengine Design fields, more particularly to Compressor test field, and in particular to a kind of axial direction
Thrust balancing device.
Background technology
During compressor rotor high-speed rotation, since Aerodynamic force action is on blade, it will generate along the forward axial force of axis,
This axial force is ultimately applied on the ball bearing of rotor, if axial force is excessive, the abrasion for causing bearing or even damage are lost
Effect, to ensure rotor safe handling, the common threaded pull rod in head is connected with rotor, and the pull rod other end acts on test-bed
To offset axial force in equipment.In prior art, axial force pull rod is located at axis centre, is only used for the axis of a rotor
To dynamic balance.The ability of balance depends on capacity of equipment, and the balanced capacity of equipment has been fixed in other words.
The content of the invention
It is an object of the invention to provide a kind of axial thrust balancing devices, overcome or alleviated by the prior art it is at least one on
State defect.
The purpose of the present invention is achieved through the following technical solutions：A kind of axial thrust balancing devices, the device are applied to double turn
Son experiment sets balancing frame at rotor portion rear, which sets a circle comb tooth row, by touching on the outside of comb tooth row
Connected components with casing wall surface to be connected in succession, and then balancing frame both sides form former and later two cavity volumes, the cavity volume casing before balancing frame
It is circumferentially opened up on wall surface and builds pressure hole, cavity volume forms high pressure chest, balance before the high pressure gas in exhaust duct is introduced balancing frame
Cavity volume leads to air to form low pressure chamber after disk, and front and rear differential pressure action offsets axial force on balancing frame.
Preferably, the comb tooth row in the balance dish external diameter is in 4 stepped arrangements, and the wherein comb tooth row is from the height
Progressively increase arrangement in the lateral low pressure chamber one side of pressure chamber one.
Preferably, the comb tooth row crown is arranged along the balancing frame radial direction, and it hangs down with the connection component
Directly it is in contact.
Preferably, set up a comb tooth group, the comb separately on the disk body of the high pressure chest one side in the balancing frame
Tooth group is twice comb tooth, and the twice comb tooth and the connection component flat contact, wherein twice comb tooth be parallel and slant setting.
Preferably, described build pressure hole is circle, and diameter and circumferentially distributed quantity are by interior stream calculation, and according to institute
The parameters such as exhaust duct stream pressure, speed and the high pressure chamber size are stated to determine.
A kind of advantageous effect of axial thrust balancing devices provided by the present invention is, for when birotor is tested
It waits, balances the axial force of another rotor；This axial thrust balancing devices by the structure design in the range of Compressor test part,
Axial force balance is realized inside compressor, is decoupled with external equipment, is more advantageous to the independent debugging of equipment.
Description of the drawings
Fig. 1 is the structure diagram of axial thrust balancing devices of the present invention.
Reference numeral：
1- exhaust ducts, 2- build pressure hole, 3- high pressure chests, 4- balancing frames, 5- low pressure chambers.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.
The axial thrust balancing devices of the present invention is described in further details below in conjunction with the accompanying drawings.
As shown in Figure 1, a kind of axial thrust balancing devices, which tests applied to birotor, is set at rotor portion rear
Put balancing frame 4,4 outer diameter of balancing frame set one circle comb tooth row, on the outside of comb tooth row crown by touch connection component with machine
Casket wall surface is connected, and then 4 both sides of balancing frame form former and later two cavity volumes, is circumferentially opened on cavity volume casing wall surface before balancing frame 4
If building pressure hole 2, cavity volume forms high pressure chest 3 before the high pressure gas in exhaust duct 1 is introduced balancing frame 4, and cavity volume leads to after balancing frame 4
Air is to form low pressure chamber 5.Wherein, in order to ensure 5 pressure of high pressure chest, vent 5 selects circular setting, diameter and circumferential direction
Distributed quantity is determined by interior stream calculation, and according to parameters such as 3 sizes of 1 stream pressure of exhaust duct, speed and high pressure chest.In order to protect
Card effectively sealing, the comb tooth row crown balanced in dish external diameter is arranged along 4 radial direction of balancing frame, and its phase vertical with connection component
Contact, and the comb tooth row sealing structure selects stepped arrangement, and the comb tooth row crown in the present embodiment specifically uses 4 ladders
The form of tooth, wherein the comb tooth row crown progressively increase arrangement from 3 one lateral 5 one side of low pressure chamber of high pressure chest, but the number of crown
Amount is not merely 4, and specific crown quantity and height are determined according to 4 pressure at both sides of balancing frame.In order to further ensure sealing
Effect selects to set up a comb tooth group separately on the disk body of 3 one side of high pressure chest in balancing frame 4, which is twice comb tooth,
The twice comb tooth and connection component flat contact, wherein twice comb tooth be parallel and the quantity of slant setting, similarly the inclination crown
It is not merely 2, it is specific to tilt crown quantity and highly determined according to 4 pressure at both sides of balancing frame.It is close so as to balance dish external diameter
Seal structure adds the form of 4 ladder teeth using 2 straight comb teeth, and comb tooth row crown flow leakage influences to drop to most on two side chambers pressure
It is small.
The concrete operating principle that balancing device of the present invention offsets axial force is described below.Air-flow is discharged into outer from exhaust duct 1
Boundary, a portion enter high pressure chest 3 from pressure hole 2 is built, and make pressure rise, low pressure chamber 5 by the comb tooth row envelope gas of obturaging of balancing frame 4
The pressure differential of logical air, chamber 3 and chamber 5 acts on balancing frame both sides with balancing axial thrust.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (5)
1. a kind of axial thrust balancing devices, which is characterized in that the device is tested applied to birotor, is set at rotor portion rear
Balancing frame (4), balancing frame (4) outer diameter set one circle comb tooth row, on the outside of comb tooth row by touch connection component with casing
Wall surface is connected, and then balancing frame (4) both sides form former and later two cavity volumes, before balancing frame (4) on cavity volume casing wall surface circumferentially
It opens up and builds pressure hole (2), cavity volume forms high pressure chest (3), balance before the high pressure gas in exhaust duct (1) is introduced balancing frame (4)
Cavity volume leads to air to form low pressure chamber (5) to disk (4) afterwards, and front and rear differential pressure action offsets axial force on balancing frame (4).
2. axial thrust balancing devices according to claim 1, which is characterized in that the comb tooth on balancing frame (4) outer diameter
Row progressively increases in 4 stepped arrangements, wherein the comb tooth row from lateral low pressure chamber (5) one side of the high pressure chest (3) one
Arrangement.
3. axial thrust balancing devices according to claim 2, which is characterized in that the comb tooth row crown is along the balancing frame
(4) radial direction is arranged, and it is touched with the connection component vertical connection.
4. axial thrust balancing devices according to claim 2, which is characterized in that in the balancing frame (4) close to the height
It presses and sets up a comb tooth group separately on the disk body of chamber (3) one side, which is twice comb tooth, the twice comb tooth and the connection group
Part flat contact, wherein twice comb tooth be parallel and slant setting.
5. axial thrust balancing devices according to claim 4, which is characterized in that pressure hole (2) of building is circle,
Diameter and circumferentially distributed quantity are by interior stream calculation, and according to the exhaust duct (1) stream pressure, speed and the high pressure chest
(3) parameters such as size determine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711341208.XA CN108105164A (en) | 2017-12-14 | 2017-12-14 | A kind of axial thrust balancing devices |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711341208.XA CN108105164A (en) | 2017-12-14 | 2017-12-14 | A kind of axial thrust balancing devices |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108105164A true CN108105164A (en) | 2018-06-01 |
Family
ID=62216042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711341208.XA Pending CN108105164A (en) | 2017-12-14 | 2017-12-14 | A kind of axial thrust balancing devices |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108105164A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111255522A (en) * | 2020-01-19 | 2020-06-09 | 中国科学院工程热物理研究所 | Balance disc structure for adjusting axial force of high-pressure rotor system of engine |
| CN112197972A (en) * | 2020-12-07 | 2021-01-08 | 中国航发上海商用航空发动机制造有限责任公司 | Axial force control device and axial force control method |
| CN112283142A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor testing device, sealing device and manufacturing method thereof |
| CN112431640A (en) * | 2020-11-11 | 2021-03-02 | 中国船舶重工集团公司第七一一研究所 | Pipeline type process gas pressure energy recovery power receiving and transmitting device and process gas pressure reduction pipeline |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1211243A (en) * | 1966-11-12 | 1970-11-04 | Zabranska Fabryka Masz Gornicz | Axial balancing arrangement in a rotodynamic pump |
| CN202194866U (en) * | 2011-07-25 | 2012-04-18 | 中国航天科技集团公司第六研究院第十一研究所 | Axial force balancing device for turbine pump of engine |
| CN204628103U (en) * | 2015-05-19 | 2015-09-09 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Balance disc rotor structure that can be used for Compressor test part |
| CN105443439A (en) * | 2015-05-19 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Exhaust casing assembly used for test piece of gas compressor |
-
2017
- 2017-12-14 CN CN201711341208.XA patent/CN108105164A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1211243A (en) * | 1966-11-12 | 1970-11-04 | Zabranska Fabryka Masz Gornicz | Axial balancing arrangement in a rotodynamic pump |
| CN202194866U (en) * | 2011-07-25 | 2012-04-18 | 中国航天科技集团公司第六研究院第十一研究所 | Axial force balancing device for turbine pump of engine |
| CN204628103U (en) * | 2015-05-19 | 2015-09-09 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Balance disc rotor structure that can be used for Compressor test part |
| CN105443439A (en) * | 2015-05-19 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Exhaust casing assembly used for test piece of gas compressor |
Non-Patent Citations (1)
| Title |
|---|
| 上海化工学院化机教研组: "《离心式压缩机》", 30 June 1978 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111255522A (en) * | 2020-01-19 | 2020-06-09 | 中国科学院工程热物理研究所 | Balance disc structure for adjusting axial force of high-pressure rotor system of engine |
| CN111255522B (en) * | 2020-01-19 | 2022-02-11 | 中国科学院工程热物理研究所 | Balance disc structure for adjusting axial force of high-pressure rotor system of engine |
| CN112431640A (en) * | 2020-11-11 | 2021-03-02 | 中国船舶重工集团公司第七一一研究所 | Pipeline type process gas pressure energy recovery power receiving and transmitting device and process gas pressure reduction pipeline |
| CN112197972A (en) * | 2020-12-07 | 2021-01-08 | 中国航发上海商用航空发动机制造有限责任公司 | Axial force control device and axial force control method |
| CN112197972B (en) * | 2020-12-07 | 2021-02-26 | 中国航发上海商用航空发动机制造有限责任公司 | Axial force control device and axial force control method |
| CN112283142A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor testing device, sealing device and manufacturing method thereof |
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Application publication date: 20180601 |