CN105971920A - Compressor test device - Google Patents
Compressor test device Download PDFInfo
- Publication number
- CN105971920A CN105971920A CN201610453633.7A CN201610453633A CN105971920A CN 105971920 A CN105971920 A CN 105971920A CN 201610453633 A CN201610453633 A CN 201610453633A CN 105971920 A CN105971920 A CN 105971920A
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- Prior art keywords
- chamber
- test device
- comb tooth
- compressor
- compressor test
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a compressor test device and relates to the technical field of engines. The compressor test device comprises a compressor, a case and a rotor driving shaft sleeve, and further comprises a drum shaft, a sealing disc and a driving shaft, wherein the sealing disc comprises a sealing cavity division part and a connecting part; labyrinth seals are arranged on the outer circumference of the sealing cavity division part and sealed with the inner chamber of the case; one end of the drum shaft is connected with the sealing cavity division part, and the other end of the drum shaft is connected with an outlet sealing disc of the compressor; the connecting part of the sealing disc is fixedly connected with one end of the rotor driving shaft sleeve, and the other end of the rotor driving shaft sleeve is connected with the driving shaft; and the sealing cavity division part divides a sealing cavity into a balance disc front cavity and a balance disc rear cavity. The compressor test device has the following beneficial effects: the sealing cavity division part divides the sealing cavity into the balance disc front cavity and the balance disc rear cavity, and the axial force born by the whole rotor system can be adjusted by controlling the pressure difference between the two cavities.
Description
Technical field
The present invention relates to technical field of engines, be specifically related to a kind of Compressor test device.
Background technology
Compressor is as one of the core component of electromotor, it is desirable to have high supercharging pressure level, high efficiency so that sending out
Motivation can obtain the higher thermal efficiency and unit power, furthermore it is required that higher surge margin is to adapt to fly
The frequent maneuvering flight of machine, it is also contemplated that versatility requirement for general purpose core scheming.Owing to air-flow is at compressor
In flowing be full UNSTEADY FLOW three-dimensional, adhesive, its flowing law is considerably complicated, up to now,
People to the understanding of the flow mechanism of gas in turbine also among constantly development and improving, the eighties
Since, Fluid Mechanics Computation obtained great progress, in terms of turbine, sent out without viscous analysis from two dimension
Exhibition is to complete three-dimensional viscosity flow analysis, and have accumulated abundant design and test experience.Since the nineties, with
The development of computer technology and computational fluid dynamics, the numerical simulation in full three-dimensional non-steady flow field obtains very
Big progress, but also have with a certain distance from practical implementation.Therefore, air-flow to be understood completely in compressor
True flow field and flowing law and the aeroperformance at off-design point, real solve compressor design
In potential problem must be by means of Compressor test and advanced means of testing.
When compressor progression is less or pressure ratio is relatively low, the balanced capacity of exerciser is sufficient for testpieces balance axle
When the demand of power.Along with the development of compressor designing technique, compressor pressure ratio and rotating speed are more and more higher,
The axial force of Compressor test part and critical speed are exactly inevitable problem, except putting down of exerciser itself
Outside weighing apparatus ability, testpieces self also to have the ability of certain balancing axial thrust, it is ensured that testpieces safety
Work reliably, it is necessary to the axial force of blance test part and the critical speed of adjustment compressor rotor, it is ensured that examination
Test the safe operation of part.
Summary of the invention
It is an object of the invention to provide a kind of Compressor test device, to solve or at least to alleviate in background technology
The problem at least one existing place.
The technical solution used in the present invention is: provide a kind of Compressor test device, comprise compressor, casing,
Rotor drive shaft set.Described Compressor test device also comprises drum barrel axle, seal pan and drive shaft；
Described seal pan comprises obturage chamber cutting part and connecting portion, described in obturage chamber cutting part excircle arrange
Comb tooth, described comb tooth is had to form sealing with the inner chamber of described casing；
One end of described drum barrel axle is connected with described chamber cutting part of obturaging, and the other end connects the outlet envelope of compressor
Tight dish；
One end that the connecting portion of described seal pan overlaps with described rotor drive shaft is fixing to be connected, and described rotor drives
The other end of axle sleeve is connected with described drive shaft；
Described chamber cutting part of obturaging chamber of obturaging is divided into balancing frame ante-chamber and balancing frame back cavity.
Preferably, described Compressor test device also comprises switching wheel disc；Described drum barrel axle comprises the first drum barrel
Axle and the second drum barrel axle, the side of described switching wheel disc connects one end of described first drum barrel axle, and opposite side is even
Connect one end of described second drum barrel axle；The other end of described first drum barrel axle connects described compressor；Described
The other end of two drum barrel axles is connected with described tight envelope chamber separating part.
Preferably, described switching wheel disc circumference uniform distribution is provided with multiple regulating block, and described regulating block is with detachably
Mode is connected with described switching wheel disc, and described regulating block can be at the radial expansion of described switching wheel disc.
Preferably, the axially arranged of described first drum barrel axle has multiple adpting flange, multiple described adpting flanges
On be provided with connecting hole, described connecting hole is for connecting described switching wheel disc by connecting bolt.
Preferably, described seal pan also comprises balance portion, described balance portion on described chamber cutting part of obturaging to
The direction away from described comb tooth to extend.
Preferably, described balance portion circumference uniform distribution is provided with multiple regulating block, and described regulating block is with detachable side
Formula is connected with the inner periphery in described balance portion, and described regulating block can be at the radial expansion in described balance portion.
Preferably, described in obturage chamber cutting part be radially arranged inside and outside double-deck comb tooth, the comb tooth of outer layer sets
Put the external peripheral surface at described chamber cutting part of obturaging, the comb tooth of internal layer be arranged on described in obturage chamber cutting part
Side, the comb tooth of outer layer and the comb tooth of internal layer all with the inner chamber formation sealing of described casing.
Preferably, the comb tooth of described outer layer is inclined teeth, and the number of teeth is at least provided with 4；The comb of described internal layer
Tooth is set to flat tooth, and the number of teeth is at least provided with 4.
Preferably, the sealing position of the comb tooth of described casing and the comb tooth of described outer layer and internal layer is provided with envelope
Tight coating.
The beneficial effects of the present invention is:
The Compressor test device of the present invention is divided into balancing frame ante-chamber by tight envelope chamber separating part chamber of obturaging
And balancing frame back cavity, by the pressure differential controlling two chambeies can regulate suffered by whole rotor-support-foundation system axial
Power.
The present invention is additionally provided with switching wheel disc, by changing installation site and the matter of switching wheel disc of switching wheel disc
Amount, can regulate the critical speed of compressor rotor.
Accompanying drawing explanation
Fig. 1 is the structural representation of the Compressor test device of one embodiment of the invention.
Fig. 2 is seal pan and the scheme of installation of switching wheel disc in the Compressor test device shown in Fig. 1.
Wherein, 1-drum barrel axle, 2-transfers wheel disc, and 3-drive shaft, 4-seal pan, 5-casing, 41-obturages
Chamber separating part, 42-connecting portion, 411-comb tooth, 412-balancing frame ante-chamber, 413-balancing frame back cavity, 43-
Balance portion, 8-compressor, 10-rotor drive shaft set, 11-the first drum barrel axle, 12-the second drum barrel axle.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, real below in conjunction with the present invention
Execute the accompanying drawing in example, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings,
The most same or similar label represents same or similar element or has same or like function
Element.Described embodiment is a part of embodiment of the present invention rather than whole embodiments.Lead to below
It is exemplary for crossing the embodiment being described with reference to the drawings, it is intended to be used for explaining the present invention, and it is not intended that right
The restriction of the present invention.Based on the embodiment in the present invention, those of ordinary skill in the art are not making creation
The every other embodiment obtained under property work premise, broadly falls into the scope of protection of the invention.Below in conjunction with
Embodiments of the invention are described in detail by accompanying drawing.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ",
"front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ",
Orientation or the position relationship of the instruction such as " outward " they are based on orientation shown in the drawings or position relationship, merely to
It is easy to describe the present invention and simplification description rather than instruction or the device of hint indication or element must have spy
Fixed orientation, with specific azimuth configuration and operation, therefore it is not intended that limit to scope
System.
As shown in Figure 1 and Figure 2, a kind of Compressor test device, comprise compressor 8, casing 5, rotor
Propeller shaft sleeve 10, described Compressor test device also comprises drum barrel axle 1, seal pan 4 and drive shaft 3.
The rear axle that rotor drive shaft set 10 is the rear fulcrum often claimed in the art described in the present embodiment
Neck.
Seal pan 4 comprises obturage chamber cutting part 41 and connecting portion 42, the excircle of chamber cutting part 41 of obturaging
Being provided with comb tooth 411, comb tooth 411 forms sealing with the inner chamber of casing 5.
In the present embodiment, chamber cutting part 41 of obturaging be radially arranged inside and outside double-deck comb tooth, outer layer
Comb tooth 411 is arranged on the external peripheral surface of chamber cutting part 41 of obturaging, and the comb tooth 411 of internal layer is arranged on to be obturaged
The side of chamber cutting part 41, the comb tooth of outer layer and the comb tooth of internal layer all with the inner chamber formation sealing of casing 5.
Have an advantage in that, advantageously form good sealing.
The comb tooth number of plies arranged on chamber separating part 41 it is understood that obturage and the quantity of each layer of tooth can
To set according to practical situation.Such as, in an alternative embodiment, obturage and arrange on chamber separating part 41
Having three layers of comb tooth, the external peripheral surface at chamber separating part 41 of obturaging is provided with one layer of comb tooth, and obturaging, chamber is divided
One layer of comb tooth it is each provided with every the both sides in portion 41.
In the present embodiment, the comb tooth 411 of described outer layer is inclined teeth, and the number of teeth is at least provided with 4；Institute
The comb tooth stating internal layer is set to flat tooth, and the number of teeth is at least provided with 4.It is understood that on outer layer comb tooth
The number of teeth might not be equal with the number of teeth on internal layer comb tooth, its quantity can set according to practical situation.Example
As, in an alternative embodiment, the comb tooth number of teeth of outer layer is 6, and the comb tooth number of teeth of internal layer is 8.
In the present embodiment, the sealing position of the comb tooth of the comb tooth of casing 5 and described outer layer and internal layer is respectively provided with
There is seal coating.Seal coating is the painting of the gap portion being coated in aircraft (aviation) engine air circulation road
Layer.The radial clearance of aircraft engine turbine often increases 0.13 millimeter, and electromotor SFC about increases
0.5%；Otherwise, reducing 0.25 millimeter, turbine efficiency improves 1%.It addition, reduce the radial clearance of compressor
The antisurging ability of electromotor can also be improved, thus improve flight safety.
One of important technology as electromotor, seal coating can improve in aircraft gas turbines and rotates with fixing
Sealing between parts, significantly improves the performance of electromotor.Use on the turbine casing with compressor
Prepare seal coating and carry out confining gas passage, reduce gap, improve the thermal efficiency.
Preferably seal coating requires that heat stability is strong, coefficient of friction is little, non-oxidizability is strong, for seal pan
And when obturaging between casing, could effectively stop scraping damage while keeping minimum clearance, reach good
Effect of obturaging.Seal coating selects composite mostly, and main component is metal phase, nonmetallic phase and hole
Gap.Wherein metal has the performances such as sprayable property, bond strength, erosion wear resistance mutually, conventional have nickel, cobalt,
Copper, aluminum etc. and alloy thereof.Nonmetallic phase provides anti-attrition, anti stickness and self-lubricating property, such as graphite, polyphenyl
Ester, kieselguhr etc..
One end of drum barrel axle 1 is connected with chamber cutting part 41 of obturaging, and the other end connects the outlet envelope of compressor 8
Tight dish；
The connecting portion 42 of seal pan 4 is fixing with one end of rotor drive shaft set 10 to be connected, rotor drive shaft set
The other end of 10 is connected with drive shaft 3；In the present embodiment, connecting portion 42 and chamber separating part 41 of obturaging
One-body molded, connecting portion 42 is protruding from the side of chamber separating part 41 of obturaging.
Chamber cutting part 41 of obturaging chamber of obturaging is divided into balancing frame ante-chamber 412 and balancing frame back cavity 413.Logical
The pressure differential crossing two chambeies of control can regulate the axial force suffered by whole rotor-support-foundation system.
In the present embodiment, Compressor test device also comprises switching wheel disc 2；Drum barrel axle 1 comprises the first drum
Cylinder axle 11 and the second drum barrel axle 12, the side of switching wheel disc 2 connects one end of the first drum barrel axle 11, separately
Side connects one end of the second drum barrel axle 12；The other end of the first drum barrel axle 11 connects compressor 8；Second
The other end of drum barrel axle 12 is connected with tight envelope chamber separating part 42.By change switching wheel disc installation site and
The quality of switching wheel disc, can regulate the critical speed of compressor rotor.
It is understood that switching wheel disc 2 circumference uniform can also be provided with multiple regulating block, described regulation
Block is removably connected with switching wheel disc 2, and described regulating block can be in the radial direction of described switching wheel disc 2
Flexible.By adjusting quantity and the position of described regulating block, the critical speed of compressor rotor can be regulated,
Ensure gas compressor stable operation.
It is understood that axially can be provided with multiple adpting flange at the first drum barrel axle 11, multiple
Being provided with connecting hole on described adpting flange, described connecting hole is for connecting described switching by connecting bolt
Wheel disc 2.By installing the switching wheel disc of different quality at diverse location, facing of compressor rotor can be regulated
Boundary's rotating speed, it is ensured that gas compressor stable operation.
In the present embodiment, seal pan 4 also comprises balance portion 43, and balance portion 43 is in described chamber segmentation of obturaging
In portion 41, the direction away from described comb tooth extends.In the present embodiment, balance portion 43 divides with chamber of obturaging
One-body molded every portion 41.It is understood that balance portion 43 can also be with chamber separating part 43 of obturaging with can
Dismounting mode connects, and has an advantage in that, the convenient planform changing balance portion 43 and quality.
It is understood that the circumference in balance portion 43 uniform can also be provided with multiple regulating block, described tune
Locking nub removably inner periphery with balance portion 43 is connected, and described regulating block can be in balance portion 43
Radial expansion.By adjusting quantity and the position of described regulating block, the critical of compressor rotor can be regulated
Rotating speed, it is ensured that gas compressor stable operation.
Last it is noted that above example is only in order to illustrate technical scheme, rather than to it
Limit.Although the present invention being described in detail with reference to previous embodiment, the ordinary skill people of this area
Member is it is understood that the technical scheme described in foregoing embodiments still can be modified by it or right
Wherein portion of techniques feature carries out equivalent；And these amendments or replacement, do not make appropriate technical solution
Essence depart from various embodiments of the present invention technical scheme spirit and scope.
Claims (9)
1. a Compressor test device, comprises compressor (8), casing (5), rotor drive shaft set
(10), it is characterised in that: described Compressor test device also comprises drum barrel axle (1), seal pan (4)
And drive shaft (3)；
Described seal pan (4) comprises obturage chamber cutting part (41) and connecting portion (42), described in obturage chamber
The excircle of cutting part (41) is provided with comb tooth (411), described comb tooth (411) and described casing (5)
Inner chamber formed seal；
One end of described drum barrel axle (1) is connected with described chamber cutting part (41) of obturaging, and the other end connects pressure
The outlet seal pan of mechanism of qi (8)；
One end of the connecting portion (42) of described seal pan (4) and described rotor drive shaft set (10) is fixed
Connecting, the other end of described rotor drive shaft set (10) is connected with described drive shaft (3)；
Described chamber cutting part (41) of obturaging will be obturaged after chamber is divided into balancing frame ante-chamber (412) and balancing frame
Chamber (413).
2. Compressor test device as claimed in claim 1, it is characterised in that: described Compressor test
Device also comprises switching wheel disc (2)；Described drum barrel axle (1) comprises the first drum barrel axle (11) and the second drum
Cylinder axle (12), the side of described switching wheel disc (2) connects one end of described first drum barrel axle (11),
Opposite side connects one end of described second drum barrel axle (12)；The other end of described first drum barrel axle (11) is even
Connect described compressor (8)；The other end of described second drum barrel axle (12) and described tight envelope chamber separating part (42)
Connect.
3. Compressor test device as claimed in claim 2, it is characterised in that: described switching wheel disc (2)
Circumference uniform distribution is provided with multiple regulating block, described regulating block removably with described switching wheel disc (2)
Connecting, described regulating block can be at the radial expansion of described switching wheel disc (2).
4. Compressor test device as claimed in claim 3, it is characterised in that: described first drum barrel axle
(11) axially arranged has multiple adpting flange, multiple described adpting flanges is provided with connecting hole, institute
State connecting hole for connecting described switching wheel disc (2) by connecting bolt.
5. Compressor test device as claimed in claim 1, it is characterised in that: described seal pan (4)
Also comprise balance portion (43), described balance portion (43) on described chamber cutting part (41) of obturaging towards far
Extend from the direction of described comb tooth.
6. Compressor test device as claimed in claim 5, it is characterised in that: described balance portion (43)
Circumference uniform distribution is provided with multiple regulating block, described regulating block removably with described balance portion (43)
Inner periphery connects, and described regulating block can be at the radial expansion of described balance portion (43).
7. Compressor test device as claimed in claim 1, it is characterised in that chamber segmentation of obturaging described in:
Portion (41) has been radially arranged inside and outside double-deck comb tooth, the comb tooth (411) of outer layer be arranged on described in obturage
The external peripheral surface of chamber cutting part (41), the comb tooth (411) of internal layer be arranged on described in obturage chamber cutting part
(41) side, the comb tooth of outer layer and the comb tooth of internal layer all with the inner chamber formation sealing of described casing (5).
8. Compressor test device as claimed in claim 7, it is characterised in that: the comb tooth of described outer layer
(411) being inclined teeth, the number of teeth is at least provided with 4；The comb tooth of described internal layer is set to flat tooth, the number of teeth
At least provided with 4.
9. Compressor test device as claimed in claim 8, it is characterised in that: described casing (5) with
The sealing position of the comb tooth of described outer layer and the comb tooth of internal layer is provided with seal coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610453633.7A CN105971920B (en) | 2016-06-22 | 2016-06-22 | A kind of Compressor test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610453633.7A CN105971920B (en) | 2016-06-22 | 2016-06-22 | A kind of Compressor test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105971920A true CN105971920A (en) | 2016-09-28 |
| CN105971920B CN105971920B (en) | 2018-01-30 |
Family
ID=57022067
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610453633.7A Active CN105971920B (en) | 2016-06-22 | 2016-06-22 | A kind of Compressor test device |
Country Status (1)
| Country | Link |
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| CN (1) | CN105971920B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989929A (en) * | 2017-04-19 | 2017-07-28 | 中国航发沈阳发动机研究所 | A kind of high-pressure compressor testpieces structure |
| CN109322848A (en) * | 2018-08-30 | 2019-02-12 | 中国航发湖南动力机械研究所 | The rotor assembly and Compressor test part of Compressor test part |
| CN109737088A (en) * | 2018-12-18 | 2019-05-10 | 南京航空航天大学 | A kind of bias compressor experimental provision |
| CN110397615A (en) * | 2019-07-31 | 2019-11-01 | 中国航发沈阳发动机研究所 | A kind of multistage compressor experimental rig |
| 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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| GB695283A (en) * | 1950-06-09 | 1953-08-05 | Dowty Equipment Ltd | Improvements relating to apparatus for supplying liquid fuel to continuous combustion turbine engines |
| JPS61272496A (en) * | 1985-05-29 | 1986-12-02 | Ebara Res Co Ltd | Axial thrust balancing device of compressor |
| CN203584577U (en) * | 2013-12-11 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Connecting structure of gas compressor and turbine |
| 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 |
| CN204921053U (en) * | 2015-05-18 | 2015-12-30 | 中国航空工业集团公司沈阳发动机设计研究所 | When double -deck comb tooth in clearance of obturaging structure of obturaging |
| 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 |
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2016
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB695283A (en) * | 1950-06-09 | 1953-08-05 | Dowty Equipment Ltd | Improvements relating to apparatus for supplying liquid fuel to continuous combustion turbine engines |
| JPS61272496A (en) * | 1985-05-29 | 1986-12-02 | Ebara Res Co Ltd | Axial thrust balancing device of compressor |
| CN203584577U (en) * | 2013-12-11 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Connecting structure of gas compressor and turbine |
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| 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 |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989929A (en) * | 2017-04-19 | 2017-07-28 | 中国航发沈阳发动机研究所 | A kind of high-pressure compressor testpieces structure |
| CN106989929B (en) * | 2017-04-19 | 2019-08-23 | 中国航发沈阳发动机研究所 | A kind of high-pressure compressor testpieces structure |
| CN109322848A (en) * | 2018-08-30 | 2019-02-12 | 中国航发湖南动力机械研究所 | The rotor assembly and Compressor test part of Compressor test part |
| CN109737088A (en) * | 2018-12-18 | 2019-05-10 | 南京航空航天大学 | A kind of bias compressor experimental provision |
| CN109737088B (en) * | 2018-12-18 | 2020-04-24 | 南京航空航天大学 | Eccentric compressor experimental device |
| CN110397615A (en) * | 2019-07-31 | 2019-11-01 | 中国航发沈阳发动机研究所 | A kind of multistage compressor experimental rig |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105971920B (en) | 2018-01-30 |
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