CN111103146A

CN111103146A - Rotary measuring device of aero-engine test bed

Info

Publication number: CN111103146A
Application number: CN201911285983.7A
Authority: CN
Inventors: 廖利华; 郭斌
Original assignee: Hunan Hanneng Technology Co Ltd
Current assignee: Hunan Hanneng Technology Co Ltd
Priority date: 2019-12-13
Filing date: 2019-12-13
Publication date: 2020-05-05

Abstract

A rotary measuring device of an aero-engine test bed is arranged on an installation mechanism of the test bed and used for measuring parameters of parts of the aero-engine, the rotary measuring device comprises two small gears, a large gear, a measuring ring and a switching piece, the two small gears are meshed with the large gear, the large gear is connected with the measuring ring, the small gears drive the large gears to rotate under the driving of a servo motor, and the large gears drive the measuring ring to rotate; a plurality of multi-measuring-point total pressure probes and a plurality of static pressure measuring holes are uniformly distributed on the measuring ring; the adapter pieces are arranged on two sides of the measuring ring and used for being connected with other components of the test bed mounting mechanism. The rotary measuring device has the advantages of accurate measurement, high efficiency, small error and the like.

Description

Rotary measuring device of aero-engine test bed

Technical Field

The invention relates to a test device for an aircraft engine component, in particular to a rotation measuring device for an aircraft engine test bed.

Background

The operating conditions of the aircraft engine are very harsh and are in a high-temperature, high-pressure and high-speed rotating operating state, and in order to improve the performance, reliability, service life and the like of the aircraft engine, the conditions of temperature, pressure, corrosion, clearance, stress and the like of the aircraft engine under different working conditions need to be fully mastered. In order to master the data, the aircraft engine is usually required to be tested on a test bed, including part and system tests, complete machine test and the like.

Particle separators are important components installed at the inlet of aircraft engines to prevent damage to engine components, increased fuel consumption and reduced engine life due to ingested particles. In order to master the technical indexes of the particle separator, the total pressure loss, total pressure distortion and other pneumatic performances of the particle separator and the flow performance caused by ice prevention need to be tested to determine whether the particle separator meets the design requirements. The existing test device can not accurately measure the airflow parameters of the test piece, and the measurement efficiency is low; the existing measuring mechanism has the problem of low measuring precision due to transmission errors of gears.

Disclosure of Invention

The invention provides a rotary measuring device of an aeroengine test bed, which solves the problems of inaccurate measurement and low precision of the existing test bed.

The technical scheme adopted by the invention is as follows:

a rotary measuring device of an aero-engine test bed is characterized in that a rotary measuring mechanism is arranged on an installation mechanism of the test bed and used for measuring parameters of parts of the aero-engine, the rotary measuring mechanism comprises two small gears, a large gear, a measuring ring and a switching piece, the two small gears are both meshed with the large gear, the large gear is connected with the measuring ring, the small gears drive the large gear to rotate under the driving of a servo motor, and the large gear drives the measuring ring to rotate; a plurality of multi-measuring-point total pressure probes and a plurality of static pressure measuring holes are uniformly distributed on the measuring ring; the adapter pieces are arranged on two sides of the measuring ring and used for being connected with other components of the test bed mounting mechanism.

Furthermore, the two pinions are identical and are both provided with the same servo motor for driving.

Furthermore, 3 total pressure probes with 5 measuring points are arranged on the rotary measuring mechanism, the total pressure probes are uniformly distributed among the probes at an angle of 120 degrees, and the measuring points of the total pressure probes are arranged according to equal sectional areas.

Further, the number of the static pressure measuring holes is 3.

Further, the transmission ratio of the small gear to the large gear is 1: 9.

Furthermore, the front end of the rotation measuring mechanism is provided with a test piece mounting mechanism, the rear end of the rotation measuring mechanism is provided with an exhaust pipe, and the rotation measuring mechanism is connected with the test piece mounting mechanism and the exhaust pipe through an adapter.

Furthermore, a sliding groove is arranged between the measuring ring and the front and rear switching sections.

Furthermore, the rotary measuring mechanism, the test piece mounting mechanism and the exhaust pipe are sealed by O-shaped rings.

Furthermore, the rotation measuring mechanism is provided with a PLC and a servo controller, and the rotation speed of the rotation measuring mechanism is controlled.

Compared with the prior art, the invention has the beneficial effects that:

two pinions are adopted to drive the large gear together, so that gear transmission errors can be effectively prevented, the precision is high, and the precision can be controlled to be 0.1 degree; the measuring ring is provided with a plurality of measuring points which are equally distributed at equal intervals by adopting a rotary measuring structure, and can cover 360 degrees after rotating a certain angle, so that the measurement is accurate and the efficiency is high.

Drawings

FIG. 1 is a block diagram of a test stand mounting system;

FIG. 2 is a diagram of a rotation measurement mechanism;

FIG. 3 is a diagram of a rotation measurement mechanism;

FIG. 4 is a cross-sectional view of a rotary measuring mechanism;

FIG. 5 is a diagram of a rotation measurement mechanism;

fig. 6 is a diagram of a rotation measuring mechanism.

Detailed Description

The invention is further illustrated by the following specific examples. The starting materials and methods employed in the examples of the present invention are those conventionally available in the market and conventionally used in the art, unless otherwise specified.

Example 1

A rotary measuring device 1 of an aircraft engine test bed is installed on the test bed as shown in figure 1, an air inlet fairing 2, a test piece installation mechanism 3, a rotary measuring mechanism 1 and an exhaust pipe 4 are sequentially arranged on the test bed to form an airflow channel, an air inlet cone 5 and an exhaust cone 6 are arranged in the airflow channel, the rotary measuring mechanism is arranged at the rear part of the test piece installation mechanism and used for measuring the airflow pressure after the test piece passes through, an air inlet pressure measuring device is arranged on the air inlet fairing, and the total airflow pressure loss and the total pressure distortion index of the test piece are calculated through a formula by measuring the air inlet pressure and the pressure parameter after the test piece passes through.

Referring to fig. 2 and 3, the rotation measuring device 1 comprises a pinion 11, a gearwheel 12, a measuring ring 13, a front adapter 15, a rear adapter 15, a servo motor 17 and a bridge. The working principle of the rotary measuring mechanism is as follows: the small teeth 11 are driven by a servo motor 17 to drive the large gear 12 to rotate, the large gear 12 and the measuring ring are coaxially arranged, and the large gear 12 drives the measuring ring to rotate. 3 total pressure probes 14 with 5 measuring points are arranged on the measuring ring 13, each probe is uniformly distributed at 120 degrees, 3 static pressure measuring holes are additionally arranged, the total number of the static pressure measuring holes is 18, and 3 total pressure measuring channels and 1 static pressure measuring channel are reserved in the measuring system. The total pressure probe measuring points are arranged according to the equal sectional area. The rotation angle of the measuring ring is 120 ℃, and the purpose that the whole exhaust annular channel can be covered by 3 probes and 3 static pressure measuring holes at 360 degrees is achieved. In this embodiment, the number of teeth of the small gear is 18, the number of teeth of the large gear is 162, the transmission ratio of the large gear to the small gear is 9, the resolution of the measurement angle is 0.04 °, and the control accuracy is 0.1 °.

As shown in fig. 4 and 5, the pinion 11 is provided with two

pinions

111, 112, which are identical, are both engaged with the gearwheels, and operate under the drive of two identical servomotors. Because gear drive has certain error and loss, adopt a pinion to be difficult to guarantee the precision, drive the gear wheel with two pinions simultaneously, can guarantee that the precision error is within 0.1.

As shown in fig. 3, polytetrafluoroethylene materials are adopted as sliding grooves between the measuring circular ring 13 and the front adapter piece and the rear adapter piece 15 of the rotary measuring mechanism, an O-shaped ring is adopted for sealing, the adapter pieces 15 are connected with other parts of the test bed and are fixed parts, the rotary circular ring 13 is a rotating part, and the sliding grooves 18 can avoid radial dry friction. And the front and rear adapter sections are sealed with the test piece and the straight exhaust pipe section by O-shaped rings 19.

When the rotation measuring mechanism is applied to a test bed, in order to realize automatic control, the rotation measuring mechanism is also provided with control equipment such as a PLC (programmable logic controller), a servo controller and the like, and the control equipment can be realized by adopting the conventional equipment.

During operation, the air flow enters from the air inlet, enters the rotary measuring device after passing through the test piece, is discharged through the exhaust pipeline, and the rotary measuring device is used for measuring the air flow parameters after passing through the test piece. A measuring ring of the rotary measuring device firstly measures a pressure flow field at a starting position, then rotates for 11 times in a clockwise direction (viewed along the air flow), measures the pressure flow field at intervals of 10 degrees, each angle position is kept in a stable running state for 3min, and a data acquisition system acquires measurement parameters of each section of a test piece and test equipment, wherein the measurement parameters comprise parameters such as atmospheric pressure, atmospheric temperature, flow, pressure and the like. After parameters such as atmospheric pressure, atmospheric temperature, flow and the like are obtained through calculation, indexes such as total pressure recovery coefficient, distortion index and the like can be obtained through the existing formula.

It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. The rotary measuring device for the test bed of the aero-engine is characterized in that the rotary measuring mechanism is arranged on an installation mechanism of the test bed and used for measuring parameters of parts of the aero-engine, the rotary measuring mechanism comprises two small gears, a large gear, a measuring ring and a switching piece, the two small gears are both meshed with the large gear, the large gear is connected with the measuring ring, the small gears drive the large gear to rotate under the driving of a servo motor, and the large gear drives the measuring ring to rotate; a plurality of multi-measuring-point total pressure probes and a plurality of static pressure measuring holes are uniformly distributed on the measuring ring; the adapter pieces are arranged on two sides of the measuring ring and used for being connected with other components of the test bed mounting mechanism.

2. The aircraft engine test stand rotation measurement device of claim 1, wherein the two pinions are identical and are each configured with an identical servomotor drive.

3. The rotary measuring device of the aero-engine test bed according to claim 1, wherein the rotary measuring mechanism is provided with 3 and 5 measuring point total pressure probes, each probe is uniformly distributed at 120 degrees, and measuring points of the total pressure probes are arranged according to equal sectional areas.

4. The aircraft engine test stand rotation measurement device of claim 1, wherein there are 3 static pressure measurement holes.

5. The aeroengine test stand rotation measurement device of claim 2, wherein the pinion gear to bull gear transmission ratio is 1: 9.

6. The aircraft engine test bed rotation measurement device of claim 1, wherein the rotation measurement mechanism is provided with a test piece mounting mechanism at the front end and an exhaust pipe at the rear end, and the rotation measurement mechanism is connected with the test piece mounting mechanism and the exhaust pipe through an adapter.

7. The aircraft engine test stand rotation measurement device of claim 1, wherein a chute is provided between the measurement ring and the front and rear transition sections.

8. The aeroengine test stand rotation measurement device of claim 6, wherein the rotation measurement mechanism is sealed with the test piece mounting mechanism and the exhaust pipe by O-rings.

9. The aircraft engine test stand rotation measurement device of claim 1, wherein the rotation measurement mechanism is provided with a PLC and a servo controller to control the rotation speed of the rotation measurement mechanism.