CN209356120U - Aero-engine axial direction power demarcates component - Google Patents
Aero-engine axial direction power demarcates component Download PDFInfo
- Publication number
- CN209356120U CN209356120U CN201920237991.3U CN201920237991U CN209356120U CN 209356120 U CN209356120 U CN 209356120U CN 201920237991 U CN201920237991 U CN 201920237991U CN 209356120 U CN209356120 U CN 209356120U
- Authority
- CN
- China
- Prior art keywords
- aero
- cap
- axial direction
- load cap
- load
- 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.)
- Active
Links
Abstract
This application provides a kind of aero-engine axial direction power to demarcate component, including load cap, centering ring and loaded seat, installation running-on is offered on the bottom surface of the loaded seat, for shaft under mounting material testing machine, ladder blind hole is offered on the upper surface of the loaded seat, the ladder blind hole is additionally provided with circular orientation protrusion for installing electrothermal tube, the upper surface of the loaded seat；The load cap is set to the circular orientation high spot, and the load cap upper surface is provided with boss, and the boss is used for connecting material testing machine upper shaft lever；The centering ring is sheathed on the junction of the circular orientation protrusion and the load cap, positions to the load cap.
Description
Technical field
This application involves aero-engine technology fields, specifically provide a kind of aero-engine axial direction power calibration component.
Background technique
In high rotary speed working, the axial load that bearing is born is likely to occur super the rotor thrust bearing of aero-engine
The case where load or light load slipping is to reduce the main reason for bearing service life leads to bearing damage.Therefore aeroplane engine is obtained
Axial force under machine real working condition and to guarantee that rotor thrust bearing rationally works in flight whole envelope by Curve guide impeller be boat
One of the key of empty engine research.
Generally use the around-France measurement aero-engine axial direction power of elastic stress both at home and abroad at present, it can by this test method
Continuously to measure and record the variation of aero-engine axial force suffered by full range of speeds internal rotor thrust bearing.
In the prior art, calibration pedestal is lain in into material and stretches machine platform, elastic stress ring is placed on pedestal and is reserved
Mounting groove in.Load cap is placed on the inner ring clearance fit on elastic ring with ring, and the press rods of material stretching-machine are vertically pushed down
Cap is loaded, stretching-machine active force is applied on elastic ring by loading cap.
But can have the following problems: calibration tooling can not be positioned with material stretching-machine；Pedestal-elastic stress ring-load
It can not be positioned between cap；Machining accuracy is low etc..
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of aero-engine axial direction power calibration groups
Part, including cap, centering ring and loaded seat are loaded, installation running-on is offered on the bottom surface of the loaded seat, for installing material
Expect shaft under testing machine, ladder blind hole is offered on the upper surface of the loaded seat, the ladder blind hole is for installing electricity
Heat pipe, the upper surface of the loaded seat are additionally provided with circular orientation protrusion；It is convex that the load cap is set to the circular orientation
At rising, the load cap upper surface is provided with boss, and the boss is used for connecting material testing machine upper shaft lever；The centering ring set
Set on the junction of the circular orientation protrusion and the load cap, the load cap is positioned.
In some embodiments, thermometer hole is offered on the side of the load cap.
In some embodiments, the thermometer hole is multiple and is uniformly distributed on the side of the load cap.
In some embodiments, fairlead is offered on the side of the load cap.
In some embodiments, multiple electrothermal tubes are provided in the ladder blind hole.
In some embodiments, the load cap is in the shape of a trumpet.
In aero-engine axial direction power calibration component provided by the embodiments of the present application, installation set is opened up in loaded seat
Mouthful, realize calibration component and Material Testing Machine positioning function；Calibration component itself and elastic stress are realized by centering ring
The positioning function of ring；External centering ring is a kind of outer location structure, facilitates installation and checks adjustment positioning accuracy；Load cap,
The fitting surface of loaded seat and elastic stress ring is the planar design of protrusion, and fitting surface self level, different components can be improved
Between the depth of parallelism realize high-precision process.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aero-engine axial direction power calibration component provided by the embodiments of the present application.
Wherein:
10, cap is loaded；11, boss；12, thermometer hole；13, fairlead；20, centering ring；30, loaded seat；31, installation set
Mouthful；32, ladder blind hole；33, circular orientation protrusion；41, Material Testing Machine upper shaft lever；42, shaft under Material Testing Machine.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related application, rather than the restriction to this application.It also should be noted that in order to
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
It should be noted that in the description of the present application, term " center ", "upper", "lower", "left", "right", "vertical",
The direction of the instructions such as "horizontal", "inner", "outside" or the term of positional relationship are direction based on the figure or positional relationship, this
It is intended merely to facilitate description, rather than indication or suggestion described device or element must have a particular orientation, with specific
Orientation construction and operation, therefore should not be understood as the limitation to the application.
In addition it is also necessary to explanation, in the description of the present application unless specifically defined or limited otherwise, term " peace
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.To those skilled in the art, it can understand that above-mentioned term exists as the case may be
Concrete meaning in the application.
Fig. 1 shows the structural schematic diagram of aero-engine axial direction power calibration component provided by the embodiments of the present application.
As shown in Figure 1, the calibration component includes load cap 10, centering ring 20 and loaded seat 30.
Installation running-on 31 is offered on the bottom surface of loaded seat 30 to load for shaft 42 under mounting material testing machine
Ladder blind hole 32 is offered on the upper surface of pedestal 30, ladder blind hole 32 is for installing electrothermal tube, the upper surface of loaded seat 30
It is additionally provided with circular orientation protrusion 33.
Load cap 10 is set at circular orientation protrusion 33, and load 10 upper surface of cap is provided with boss 11, and boss 11 is used for
Connecting material testing machine upper shaft lever 41.Optionally, load cap 10 is in the shape of a trumpet, is buckled in loaded seat 30.
Optionally, multiple thermometer holes 12 are offered on the side of load cap 10, and multiple thermometer holes 12 are uniformly distributed
In load cap 10 side on, for example, load cap side on sustained height, be evenly distributed with multiple thermometer holes 12, it is multiple
Thermometer hole 12 is distributed on same circumference.
Optionally, fairlead 13 is offered on the side of load cap 10, multiple electric heating is provided in ladder blind hole 32
Pipe, the lead of electrothermal tube can be pierced by from fairlead 13.
Centering ring 30 is sheathed on the junction of circular orientation protrusion 33 with load cap 10, positions to load cap 10.?
In use, elastic stress ring is placed at circular orientation protrusion 33, then load cap is placed on elastic stress ring, and
Its outer sheath centering ring 30, to be positioned to elastic stress ring and load cap 10, then by Material Testing Machine upper shaft lever and
Lower shaft carries out load test to the calibration component.
Optionally, the outer diameter of lower end surface and the matching for elastic stress ring for loading cap 10, load the lower end surface of cap 10
Internal diameter is less than elastic stress ring.
Optionally, the internal diameter of circular orientation protrusion 33 is less than elastic stress ring, and outer diameter matches with elastic stress ring, annular
Positioning protrusion 33 uses surface carburization process, so as to improve service life.
Optionally, the lower end surface of cap 10 is loaded, the flatness of circular orientation protrusion 33 is 0.02.
So far, it has been combined preferred embodiment shown in the drawings and describes the technical solution of the application, still, this field
Technical staff is it is easily understood that the protection scope of the application is expressly not limited to these specific embodiments.Without departing from this
Under the premise of the principle of application, those skilled in the art can make equivalent change or replacement to the relevant technologies feature, these
Technical solution after change or replacement is fallen within the protection scope of the application.
Claims (6)
1. a kind of aero-engine axial direction power demarcates component, which is characterized in that including load cap (10), centering ring (20) and load
Pedestal (30),
Installation running-on (31) is offered on the bottom surface of the loaded seat (30), is used for shaft (42) under mounting material testing machine,
It is offered on the upper surface of the loaded seat (30) ladder blind hole (32), the ladder blind hole (32) is for installing electric heating
Pipe, it is raised (33) that the upper surface of the loaded seat (30) is additionally provided with circular orientation；
The load cap (10) is set at the circular orientation raised (33), and load cap (10) upper surface is provided with boss
(11), the boss (11) is used for connecting material testing machine upper shaft lever (41)；
The centering ring (20) is sheathed on the junction of the circular orientation raised (33) and load cap (10), adds to described
Cap (10) are carried to be positioned.
2. aero-engine axial direction power according to claim 1 demarcates component, which is characterized in that load cap (10)
Thermometer hole (12) are offered on side.
3. aero-engine axial direction power according to claim 2 demarcates component, which is characterized in that the thermometer hole (12) is
It is multiple and be uniformly distributed in it is described load cap (10) side on.
4. aero-engine axial direction power according to claim 1 demarcates component, which is characterized in that load cap (10)
Fairlead (13) are offered on side.
5. aero-engine axial direction power according to claim 1 demarcates component, which is characterized in that the ladder blind hole (32)
Inside it is provided with multiple electrothermal tubes.
6. aero-engine axial direction power according to claim 1 demarcates component, which is characterized in that the load cap (10) is in
Bell mouth shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920237991.3U CN209356120U (en) | 2019-02-26 | 2019-02-26 | Aero-engine axial direction power demarcates component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920237991.3U CN209356120U (en) | 2019-02-26 | 2019-02-26 | Aero-engine axial direction power demarcates component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209356120U true CN209356120U (en) | 2019-09-06 |
Family
ID=67803773
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920237991.3U Active CN209356120U (en) | 2019-02-26 | 2019-02-26 | Aero-engine axial direction power demarcates component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209356120U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116380337A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Axial force calibration device of squirrel-cage stress ring composite structure |
-
2019
- 2019-02-26 CN CN201920237991.3U patent/CN209356120U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116380337A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Axial force calibration device of squirrel-cage stress ring composite structure |
| CN116380337B (en) * | 2023-06-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Axial force calibration device of squirrel-cage stress ring composite structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103591878B (en) | Engine assembly device and assembly method | |
| CN209356120U (en) | Aero-engine axial direction power demarcates component | |
| CN106289734A (en) | A kind of aero-engine casing high temperature containment test technology | |
| US11609165B2 (en) | Material performance testing system under fixed multi-field coupling effect in hypergravity environment | |
| CN111238711B (en) | Rotor axial force testing method | |
| US9991009B2 (en) | Electrical feedthroughs for nuclear reactor | |
| CN106404412B (en) | It is a kind of for measuring the device of Aero-engine Bearing seat center displacement | |
| WO2020252984A1 (en) | Material performance testing system under suspension multi-field coupling action in supergravity environment | |
| CN109855872A (en) | A kind of general roller bearing testing machine | |
| CN104215441B (en) | A kind of vertical rotor dynamic radial load maintainer and stability test scheme | |
| CN107687831B (en) | Aero-engine turn, stator radial clearance calculation method | |
| EP3153813B1 (en) | Measuring relative concentricity deviations in a confined space between two circumferential elements | |
| EP2362967B1 (en) | Apparatus and method for automatically and remotely measuring the internal gap of a reactor | |
| CN105651408A (en) | Aero-engine exhaust gas temperature sensor | |
| CN113280962A (en) | Axial load detection device of turntable bearing and shield machine | |
| CN205991798U (en) | A kind of wheel hub axial direction clearance detector | |
| JP2016509234A (en) | Method and apparatus for measuring tube pressure | |
| CN109883610A (en) | Aero-engine axial direction power measurement heating calibration furnace | |
| CN208818131U (en) | Tooling is examined in the installation of large-sized low-speed exhaust valve of marine diesel engine conical ring | |
| CN107402032B (en) | A kind of multiple spot conversion equipment of revolving part wall surface parameter measurement | |
| CN113984243B (en) | Temperature detecting device | |
| CN218973405U (en) | Automobile clutch controller ACU lower shell detection positioning platform | |
| CN219200322U (en) | Concentricity detects frock | |
| CN113944860B (en) | Support structure for reactor level gauge | |
| CN116106020B (en) | Fixing frame for measuring frequency of combustion chamber of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |