CN205280368U - Measuring device is always pressed to experimental radial multiple spot of high thrust engine distortion - Google Patents
Measuring device is always pressed to experimental radial multiple spot of high thrust engine distortion Download PDFInfo
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- CN205280368U CN205280368U CN201521047520.4U CN201521047520U CN205280368U CN 205280368 U CN205280368 U CN 205280368U CN 201521047520 U CN201521047520 U CN 201521047520U CN 205280368 U CN205280368 U CN 205280368U
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Abstract
The utility model discloses a belong to engine fluid total pressure measurement field, relate to the experimental total pressure measurement of aeroengine distortion, experimental AIP (Aerodynamic interface plane) the radial multiple spot parameter measurement in cross -section of mainly used high thrust engine inlet total pressure distortion. This measuring device global architecture adopts single cantilever beam equal strength integral structure, including radome fairing, the thin steel pipe of biography dabbing, integration bracing piece, mistake proofing mounting panel, circular adapter, pressure spigot joint, glass cotton fiber dimension. It is fixed together as rectification pressure sensing gauge head wherein to pass the thin steel pipe of dabbing and radome fairing, be fixed in integrated bracing piece assigned position on, radial multiple spot passes the thin steel pipe of dabbing and draws forth through integration bracing piece inner chamber and transmit to the pressure spigot joint, passes through the pressure collecting system again, the computer is given in final transmission. The glass cotton fiber dimension passes the thin steel pipe of dabbing protection, fixed to the branch intracavity, circular adapter is used for a plurality of pressure measurement stations to pass the switching of the thin steel pipe of dabbing, protection, fixed, the integration bracing piece is fixed on the mistake proofing mounting panel, and the measuring device of being convenient for installs and use. This measuring device boom length is not less than 325mm, always presses insensitive angle to be not less than 25, engine inlet AIP cross -section and blocks up than being not more than 5%.
Description
Technical field
This utility model patent belongs to engine fluid total pressure measurement field, is mainly used in test AIP (AerodynamicInterfacePlane) the cross-section radial multiple spot stagnation pressure parameter measurement of high thrust motor inlet total pressure distortion.
Background technology
High thrust motor aberration test radially multiple spot parameter measuring apparatus abroad has cantilever beam structure form, also has Snap ring structure form, is respectively arranged with pluses and minuses. Cantilever beam structure is installed, dismounting is simple, and flow field disturbance is little, compact conformation, and traditional structure support bar root exists obvious stress and concentrates; Snap ring form structure is complicated, installs, dismantles difficulty, and flow field disturbance is big, offsets except Root Stress has certain effect, but introduces mount stress. Domestic following external respective design, tradition branching rod structure is designed with thin walled bar version. Count to meet radially cloth, measure the technical specifications such as cross sectional occlusion ratio, certainty of measurement, limit measurement apparatus and there is " elongated " architectural feature, cause that first natural frequency is on the low side, it is easy to resonance fatigue occurs in aberration test complex vibration environment, causes Strength Failure. Aberration test process exists the phenomenon of support bar fracture, electromotor is caused serious damage; High thrust motor aberration test is usually present and meets radial direction measuring point quantity and intensity of probe cannot ensure, delete radially measuring point, the way of compromise test demand, it is impossible to measure aberration test AIP kernel of section flow field data, performance that electromotor is distorted accurately is evaluated and is caused very big impact.
Utility model content
The purpose of the present invention: provide that a kind of intensity is reliable, compact conformation, easy installation and removal, flow field disturbance is little, certainty of measurement is high, good in economic efficiency, can be used for high thrust motor inlet airflow distortion test AIP cross-section radial multiple spot total pressure measure apparatus, the accurately evaluation for electromotor distortion performance provides test guarantee.
Technical scheme: for the complexity of high thrust motor total pressure distortion experimental enviroment, Conventional distortion is tested the performance of measurement apparatus Strength Failure, failure mechanism systematic analysis, it is proposed to improving measurement apparatus natural frequency and eliminating support bar stress to greatest extent and concentrate is that aberration test radially Multi point measuring apparatus is opened one's minds. Population structure adopts single cantilever beam equal strength integral structure. It is spigot joint that this measurement apparatus mainly includes trousers, pressure transmission capillary tubing, integration support bar, microglass fiber, mistake proofing installing plate, circular adapter, pressure. Attached harvester includes switching pipeline, pressure acquisition module, computer etc.
Wherein, trousers, for high-velocity fluid rectification stagnation, increasing the insensitive angle of measurement apparatus stagnation pressure, improves certainty of measurement;
Pressure transmission capillary tubing is used for pressure-sensing, propagation;
Integration support bar, for radially multiple stagnation pressure measuring points are supported, fixed, adopts single cantilever beam strength structure, and fluoran stream surface transition is widened, root rounding off. Support bar processing integrated with mounting seat, substantially increases measurement apparatus natural frequency, significantly eliminates pole Root Stress and concentrates;
Mistake proofing installing plate is used for the installation of measurement apparatus, fixes, and comes the location of flow path direction.
Circular adapter supports for the switching of radially multiple stagnation pressure measuring points, extraction; Structural design adopts circular configuration, compact conformation, safe and reliable;
Pressure is spigot joint for pressure-measuring-point switching, sealing.
Beneficial effects of the present invention: the present invention radially multiple spot total pressure measure apparatus has obtained successful Application in many types of high thrust aero-engine total pressure distortion is tested, measurement apparatus radially cloth is counted, blockage ratio, certainty of measurement are satisfied by test and test specification requirement, accurately obtain engine intake AIP cross section always to have a meeting, an audience, etc. well under one's control, successfully avoid the way deleting radially measuring point in high thrust motor total pressure distortion process of the test, the accurately evaluation for high thrust motor total pressure distortion performance is laid a good foundation.
Accompanying drawing explanation
Fig. 1 high thrust motor aberration test is multiple spot total pressure measure apparatus structure chart radially
(1) trousers: high-velocity fluid rectification stagnation;
(2) pressure transmission capillary tubing: pressure-sensing and propagation;
(3) microglass fiber: integration support bar inner chamber is fixing to the protection of pressure transmission capillary tubing;
(4) integration support bar: radially the support of multiple stagnation pressure measuring points is with fixing;
(5) mistake proofing installing plate: the installation of measurement apparatus is with fixing;
(6) circular adapter: the extraction of multiple stagnation pressure measuring points is fixing to be supported;
(7) pressure is spigot joint: multiple stagnation pressure measuring point pressure are transferred.
Fig. 2 is the partial sectional view of Fig. 1.
Detailed description of the invention
Below by detailed description of the invention, the present invention is described in further detail:
Referring to Fig. 1, it is spigot joint that high thrust motor aberration test of the present invention radially multiple spot total pressure measure apparatus includes trousers, many pressure transmission capillary tubings, microglass fiber, integration support bar, mistake proofing installing plate, circular adapter, pressure.
The rectified cover rectification stagnation of engine intake high velocity air, incoming flow dynamic pressure stagnation is converted into stagnation pressure, spigot joint to pressure through the transmission of pressure transmission capillary tubing, is sent to acquisition system by pressure switching device, it is achieved the measurement of stagnation pressure. Trousers external form is cylindrical structural, external diameterInternal diameterBleeder port is 2, diameter The bleeder port area of trousers is designed as 0.26��0.39 with the ratio of circulation area. The quality of dome structure, diameter affects total pressure measurement precision. The too thin reliability of pressure transmission capillary tubing is poor, it is easy to damaged, and too slightly can affect total pressure measurement response speed, and general external diameter is chosen asPressure transmission capillary tubing is fixed on trousers typically via pressure welding techniques, it is desirable to trousers and pressure transmission capillary tubing are just to carrying out flow path direction, in order to improve insensitive angle, and mouth of pipe chamfered. Trousers is generally adopted argon arc welding or laser welding technology is fixed on integration support bar and radially specifies position, realizes engine intake difference radial height stagnation pressure parameter measurement.
Integration support bar adopts the high intensity modulated structure Steel Bar integration that yield strength is not less than 600MPa to process, population structure adopts single cantilever beam strength structure, in order to reduce the impact of stream field, fluoran stream surface rounding off, from the beginning widen gradually to root, root rounding off, integration support bar inner chamber adopts linear cutter to form. Pressure transmission capillary tubing is when support bar inner chamber cabling; do not allow to further exceptionally straight; bending radius is not less than 4D (D is pressure transmission capillary tubing external diameter); it is generally adopted special tooling to bend cabling; after cabling completes; adopt microglass fiber that the protection of pressure transmission capillary tubing is fixing, it is prevented that in use to cause the damage of pressure transmission capillary tubing because supporting vibration of bar. Installing plate is designed as Anti-error structure, has incoming flow locating surface, adopts flange connection. The trim designs of mistake proofing installing plate and support bar misplaces location structure, and with the welding boss of 5mm, installation base and installing plate R4mm rounding off, welding manner adopts argon arc welding butt welded seam defect detecting test, meets flaw detection requirement. Radially multiple pressure-measuring-point pressure transmission capillary tubings are carried out switching and support by circular adapter, compact conformation, and reliability is high, and erection welding adopts argon arc welding or soldering. Pressure spigot joint employing 60 �� of inner cones, ball face sealing structures, pressure height, structure is reliable, and erection welding mode adopts argon arc welding or soldering.
This measurement apparatus jib-length is not less than 325mm, and the insensitive angle of stagnation pressure is not less than �� 25 ��, and engine intake AIP cross sectional occlusion ratio is not more than 5%. Measurement apparatus radially cloth is counted and is generally 4��6 points, generally installs and uses 4��8, adopts the arrangement that circumference is uniform, flange installation structure, is in use furnished with fine copper gasket seal.
Claims (2)
1. a high thrust motor aberration test radially multiple spot total pressure measure apparatus, it is characterized in that, adopt single cantilever beam equal strength integral structure, including trousers (1), pressure transmission capillary tubing (2), microglass fiber (3), integration support bar (4), mistake proofing installing plate (5), circular adapter (6), pressure spigot joint (7); Wherein trousers (1) trousers overall dimensions are not more thanIt is fixed together as rectification pressure-sensitive gauge head with pressure transmission capillary tubing (2), it is fixed in integration support bar (4), radially multiple spot stagnation pressure transmits to pressure spigot joint (7) at integration support bar (4) inner chamber through pressure transmission capillary tubing (2), then through pressure acquisition system, finally it is transferred to computer; Pole intracavity pressure transmission capillary tubing (2) is protected, is fixed by microglass fiber (3); Circular adapter (6) is transferred for multiple stagnation pressures measuring point pressure transmission capillary tubing (2), protects, is fixed; Integration support bar (4) is fixed on mistake proofing installing plate (5), it is simple to installing and using of measurement apparatus.
2. high thrust motor aberration test according to claim 1 radially multiple spot total pressure measure apparatus, it is characterised in that: body support bar (4) adopts the high intensity modulated structure Steel Bar integration processing that yield strength is not less than 600MPa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521047520.4U CN205280368U (en) | 2015-12-15 | 2015-12-15 | Measuring device is always pressed to experimental radial multiple spot of high thrust engine distortion |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521047520.4U CN205280368U (en) | 2015-12-15 | 2015-12-15 | Measuring device is always pressed to experimental radial multiple spot of high thrust engine distortion |
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| Publication Number | Publication Date |
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| CN205280368U true CN205280368U (en) | 2016-06-01 |
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| CN201521047520.4U Active CN205280368U (en) | 2015-12-15 | 2015-12-15 | Measuring device is always pressed to experimental radial multiple spot of high thrust engine distortion |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116046403A (en) * | 2023-04-03 | 2023-05-02 | 中国航发四川燃气涡轮研究院 | Engine inlet large-span total pressure distribution measuring device |
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2015
- 2015-12-15 CN CN201521047520.4U patent/CN205280368U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116046403A (en) * | 2023-04-03 | 2023-05-02 | 中国航发四川燃气涡轮研究院 | Engine inlet large-span total pressure distribution measuring device |
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Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 operation monitoring department, mailbox 305, Jiangyou, Sichuan, Mianyang, Sichuan Patentee before: CHINA GAS TURBINE EST |