CN113984183A - Monitoring method for horizontal vibration of aircraft engine - Google Patents
Monitoring method for horizontal vibration of aircraft engine Download PDFInfo
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- CN113984183A CN113984183A CN202111225569.4A CN202111225569A CN113984183A CN 113984183 A CN113984183 A CN 113984183A CN 202111225569 A CN202111225569 A CN 202111225569A CN 113984183 A CN113984183 A CN 113984183A
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 15
- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000001133 acceleration Effects 0.000 claims description 9
- 239000002184 metal Substances 0.000 claims description 9
- 230000001939 inductive effect Effects 0.000 claims 2
- 230000011664 signaling Effects 0.000 claims 1
- 238000005259 measurement Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000003745 diagnosis Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H11/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties
- G01H11/02—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by magnetic means, e.g. reluctance
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H11/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties
- G01H11/06—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means
- G01H11/08—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means using piezoelectric devices
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
- G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
- G01P15/08—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values
- G01P15/09—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values by piezoelectric pick-up
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention belongs to the field of measurement and control of aero-engines, and particularly relates to a method for monitoring horizontal vibration of an aero-engine. The technical scheme of the invention is as follows: a support is vertically arranged on the mounting edge of an intermediate casing of an engine, a horizontal vibration sensor and a vibration speed converter are respectively assembled at two ends of the support, a vibration signal of the engine is collected in the horizontal direction perpendicular to the axis of the engine, and the signal is transmitted to a comprehensive controller to judge the vibration condition of the engine. The invention adopts two types of sensors with different working principles to jointly acquire vibration signals of the engine in the horizontal direction, simultaneously transmits the vibration signals to the integrated controller for comparison, judges the vibration condition of the engine by utilizing the comparison condition of the output signals of the two annunciators, controls the state of the engine, realizes accurate judgment of the vibration condition of the engine, and avoids the output signal distortion caused by the failure of the sensor from influencing the work of the engine.
Description
Technical Field
The invention belongs to the field of measurement and control of aero-engines, and particularly relates to a method for monitoring horizontal vibration of an aero-engine.
Background
The vibration of the aircraft engine is a fatal factor influencing the use of the engine, the vibration of the aircraft engine is a reflection of the working state of the engine, and the accurate monitoring of the vibration condition of the engine is an effective reaction of the vibration condition of the engine and is a basis for judging whether the engine can normally work or not. At present, a frequency type vibration sensor is mounted on an intermediate casing of an engine to measure the vibration condition of the engine, if the sensor fails or performance is attenuated, a measured signal is distorted, the condition of the engine and a signal false alarm cannot be accurately reflected, so that a pilot misjudges, the normal flight task of the airplane is influenced, even the engine stops, the flight safety of the airplane is influenced, and the judgment and control on the condition of the engine are influenced.
Disclosure of Invention
The invention provides a method for monitoring horizontal vibration of an aircraft engine, which adopts two types of sensors with different working principles to jointly acquire vibration signals in the horizontal direction of the engine and simultaneously transmit the vibration signals to a comprehensive controller for comparison, judges the vibration condition of the engine by utilizing the comparison condition of the output signals of the two annunciators, controls the state of the engine, realizes accurate judgment of the vibration condition of the engine, and avoids the output signal distortion caused by the failure of the sensor from influencing the work of the engine.
The technical scheme of the invention is as follows:
a support is vertically arranged on the mounting edge of an intermediate casing of an engine, a horizontal vibration sensor and a vibration speed converter are respectively assembled at two ends of the support, a vibration signal of the engine is collected in the horizontal direction perpendicular to the axis of the engine, and the signal is transmitted to a comprehensive controller to judge the vibration condition of the engine.
Further, according to the monitoring method for the horizontal vibration of the aircraft engine, the horizontal vibration sensor comprises a coil which is static relative to the sensor shell and a magnet which induces the vibration, the magnet and the coil move relatively, and the coil induces an electromotive force which is proportional to the vibration speed of the engine and sends a signal.
Further, the method for monitoring the horizontal vibration of the aircraft engine comprises the steps that the vibration speed converter comprises a metal shell, a piezoelectric acceleration converter, an electronic instrument assembly and a mounting stud, the piezoelectric acceleration converter and the electronic instrument assembly are arranged in the metal shell, and the mounting stud is arranged at the end head of the metal shell; the piezoelectric acceleration transducer converts the vibration of the engine into an electronic signal proportional to the vibration, and the signal is processed by the electronic instrument assembly and then emitted.
Furthermore, according to the method for monitoring the horizontal vibration of the aircraft engine, a threaded through hole is formed in the center of the bracket, and the vibration speed converter is fixedly installed on the bracket by screwing the installation stud into the threaded through hole; the horizontal vibration sensor and the vibration speed converter are fixedly arranged on the bracket in a symmetrical state, so that the sensed surface of the vibration speed converter is tightly attached to the sensed surface of the horizontal vibration sensor.
The invention has the beneficial effects that:
(1) double margin control is adopted, and the reliability is high; the vibration sensor which adopts two types of different working principles and generates different types of signals is adopted to simultaneously measure the vibration condition of the same position, and the two signals are compared to better ensure the measurement accuracy of the vibration condition of the engine.
(2) Accurately measuring the horizontal vibration condition of the engine; the two vibration signals are mutually complementary, and false alarm control caused by signal distortion caused by failure of one sensor is avoided.
(3) The assembly is simple and convenient; in the direction perpendicular to the intermediate casing, the two sensors are attached and mounted through one support, and the mounting method is simple, convenient and easy to implement.
Drawings
FIG. 1 is a schematic view of a horizontal vibration sensor and a vibration speed converter mounted on an intermediate case mounting edge of an engine through a bracket;
FIG. 2 is a schematic diagram of a horizontal vibration sensor;
FIG. 3 is a schematic diagram of a vibration speed transducer configuration;
fig. 4 is a schematic diagram of a vibration information monitoring system.
Detailed Description
As shown in fig. 1-3, in a method for monitoring horizontal vibration of an aircraft engine, a bracket 2 is vertically installed on an intermediate casing installation edge 1 of the engine, a horizontal vibration sensor 3 and a vibration speed converter 4 are respectively installed at two ends of the bracket 2, a threaded through hole is formed in the center of the bracket 2, and the vibration speed converter 4 is fixedly installed on the bracket 2 by screwing a mounting stud 11 into the threaded through hole; the horizontal vibration sensor 3 and the vibration speed converter 4 are fixedly arranged on the bracket 2 in a symmetrical state, so that the sensing surface of the vibration speed converter 4 is tightly attached to the sensing surface of the horizontal vibration sensor 3;
the horizontal vibration sensor 3 comprises a coil 6 which is static relative to the sensor shell 5 and a magnet 7 which induces vibration, the magnet 7 and the coil 6 generate relative movement, the coil 6 induces electromotive force which is proportional to the vibration speed of the engine and sends out signals; the working principle of the device is based on the electromagnetic induction phenomenon, and mechanical vibration acting on the axial direction is converted into voltage proportional to the vibration speed;
the vibration speed converter 4 comprises a metal shell 8, a piezoelectric acceleration converter 9, an electronic instrument assembly 10 and a mounting stud 11, wherein the piezoelectric acceleration converter 9 and the electronic instrument assembly 10 are arranged inside the metal shell 8, and the mounting stud 11 is arranged at the end head of the metal shell 8; the piezoelectric acceleration transducer 9 converts the vibration of the engine into an electronic signal proportional to the vibration, and the signal is processed by the electronic instrument component 10 and then emitted; the working principle is based on the direct piezoelectric effect phenomenon, and mechanical vibration acting on the axis direction of an engine is converted into an electronic signal proportional to the vibration speed;
and acquiring a vibration signal of the engine in a horizontal direction perpendicular to the axis of the engine, and transmitting the signal to the integrated controller to judge the vibration condition of the engine.
As shown in fig. 4, signals of a horizontal vibration sensor 3 and a vibration speed converter 4 are transmitted to an engine integrated controller, the horizontal vibration sensor 3 is used for forming a discrete alarm signal, and the vibration speed converter 4 is used for checking a vibration signal of the engine after flying. The vibration signal and the discrete alarm signal from the engine integrated controller are transmitted to each monitoring device along the communication bus: to a multi-function display for display, to a voice warning system for warning, and to an information diagnosis device for engine condition diagnosis.
Claims (4)
1. A method for monitoring horizontal vibration of an aircraft engine is characterized in that a bracket is vertically mounted on a mounting edge of an intermediate casing of the engine, a horizontal vibration sensor and a vibration speed converter are respectively mounted at two ends of the bracket, a vibration signal of the engine is acquired in the horizontal direction perpendicular to the axis of the engine, and the signal is transmitted to a comprehensive controller to judge the vibration condition of the engine.
2. A method of monitoring the horizontal vibration of an aircraft engine as claimed in claim 1, wherein said horizontal vibration sensor comprises a coil stationary relative to the sensor housing and a vibration-inducing magnet, said magnet and said coil moving relative to each other, said coil inducing an electromotive force proportional to the speed of engine vibration and signaling the electromotive force.
3. The method of monitoring the horizontal vibration of an aircraft engine according to claim 1, wherein the vibration speed converter comprises a metal shell, a piezoelectric acceleration converter, an electronic component and a mounting stud, the piezoelectric acceleration converter and the electronic component are disposed inside the metal shell, and the mounting stud is disposed at the end of the metal shell; the piezoelectric acceleration transducer converts the vibration of the engine into an electronic signal proportional to the vibration, and the signal is processed by the electronic instrument assembly and then emitted.
4. The method for monitoring the horizontal vibration of the aircraft engine as claimed in claim 3, wherein a threaded through hole is formed in the center of the bracket, and the vibration converter is fixedly mounted on the bracket by screwing the mounting stud into the threaded through hole; the horizontal vibration sensor and the vibration speed converter are fixedly arranged on the bracket in a symmetrical state, so that the sensed surface of the vibration speed converter is tightly attached to the sensed surface of the horizontal vibration sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111225569.4A CN113984183A (en) | 2021-10-21 | 2021-10-21 | Monitoring method for horizontal vibration of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111225569.4A CN113984183A (en) | 2021-10-21 | 2021-10-21 | Monitoring method for horizontal vibration of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113984183A true CN113984183A (en) | 2022-01-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111225569.4A Pending CN113984183A (en) | 2021-10-21 | 2021-10-21 | Monitoring method for horizontal vibration of aircraft engine |
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| Country | Link |
|---|---|
| CN (1) | CN113984183A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048106A (en) * | 2012-12-26 | 2013-04-17 | 成都发动机（集团）有限公司 | Aeroengine vibration transducer double-wire checking and detecting method and implementation system thereof |
| CN206208528U (en) * | 2016-09-30 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Aero-engine vibration-testing apparatus |
| CN107389337A (en) * | 2017-06-13 | 2017-11-24 | 中国航发湖南动力机械研究所 | Aeroengine rotor vibration test system |
| CN108021122A (en) * | 2017-12-12 | 2018-05-11 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine vibration-testing trouble-shooter and diagnostic method |
| CN110987152A (en) * | 2019-11-27 | 2020-04-10 | 苏州长风航空电子有限公司 | High-precision magnetoelectric vibration measuring device for aviation |
-
2021
- 2021-10-21 CN CN202111225569.4A patent/CN113984183A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048106A (en) * | 2012-12-26 | 2013-04-17 | 成都发动机（集团）有限公司 | Aeroengine vibration transducer double-wire checking and detecting method and implementation system thereof |
| CN206208528U (en) * | 2016-09-30 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Aero-engine vibration-testing apparatus |
| CN107389337A (en) * | 2017-06-13 | 2017-11-24 | 中国航发湖南动力机械研究所 | Aeroengine rotor vibration test system |
| CN108021122A (en) * | 2017-12-12 | 2018-05-11 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine vibration-testing trouble-shooter and diagnostic method |
| CN110987152A (en) * | 2019-11-27 | 2020-04-10 | 苏州长风航空电子有限公司 | High-precision magnetoelectric vibration measuring device for aviation |
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