CN205841014U - A kind of gas turbine starter outfield running parameter detection device - Google Patents
A kind of gas turbine starter outfield running parameter detection device Download PDFInfo
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- CN205841014U CN205841014U CN201620648927.0U CN201620648927U CN205841014U CN 205841014 U CN205841014 U CN 205841014U CN 201620648927 U CN201620648927 U CN 201620648927U CN 205841014 U CN205841014 U CN 205841014U
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- gas turbine
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- turbine starter
- outfield
- starter
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Abstract
A kind of gas turbine starter outfield running parameter detection device, it includes detecting main frame, detection cable, described detection cable is threeway cable, described detection cable is provided with the first joint for being connected with described detection main frame, for the second joint being connected with described cable, and for the 3rd joint being connected with described gas turbine starter, described detection main frame is provided with power supply, multiple signal lights, gasifier speed table, free turbine tachoscope, electric starter line voltmeter, exhaust gas thermometer and self-inspection knob.A kind of gas turbine starter outfield provided by the utility model running parameter detection device, the working condition of each electric attachments and gas turbine starter can be checked in situ, can quickly position gas turbine starter failure cause and position, improve outfield troubleshooting efficiency and shorten the troubleshooting cycle.
Description
Technical field
This utility model relates to aero-engine field, rises particularly to a kind of gas turbine to aviation turbofan engine
Motivation outfield running parameter detection device.
Background technology
Gas turbine starter is a kind of small sized turbine shaft generator, as the auxiliary power of the many types of fanjet of China
Device, provides the power needed for starting, false start, blowdown firing by power output shaft to fanjet, and can send out at turbofan
When motivation does not works, provide power for power system and hydraulic system.Therefore gas turbine starter normally works, and is that turbofan is sent out
The basic premise that motivation or even whole airplane normally use.
From the point of view of structural principle, gas turbine starter is a basic complete engine system, usual gas turbine
Starter has multiple accessory cables connector, is connected with aircraft control unit by cable and to carry out signal mutual: combustion gas whirlpool
Gasifier speed sensor on wheel starter, free turbine speed probe, thermocouple, minimum lubricating oil pressure signal
Device, motor disengage the electric attachments such as signal indicator and the running parameter of starter are transferred to aircraft control unit, electric starter, parking
The electric attachments such as solenoid valve, slow train solenoid valve, Power Component solenoid valve, ignition coil receive and perform aircraft and control single
The control signal of unit.
Substantial amounts of parameter and signal can be produced, these parameters and signal reflection gas turbine during gas turbine starter work
The duty of starter, to analyzing, gas turbine starter fault is significant.But owing to gas turbine starter exists
It is only used as a type adnexa of fanjet on aircraft, therefore the instrument of aircraft and FDR system all do not gather its running parameter,
Do not reserve dedicated test interface.
Therefore, when gas turbine starter breaks down in outfield, it is impossible to directly measure parameter and signal, this is impact
The main unfavorable factor of on-the-spot troubleshooting.This situation causes gas turbine starter, and when breaking down in outfield, troubleshooting means are very
Limited, return factory and lead high, while affecting user's use, also bring bigger economic loss to factory.
Utility model content
The technical problems to be solved in the utility model is to provide a kind of gas turbine starter outfield running parameter detection dress
Put, so that noted earlier problem is reduced or avoided.
For solving above-mentioned technical problem, the utility model proposes the running parameter detection of a kind of gas turbine starter outfield
Device, it is for carrying out the gas turbine starter being connected with aircraft control unit by multiple cables installed aboard
Running parameter detects, and it includes detecting main frame, detection cable, and described detection cable is threeway cable, and described detection cable is arranged
There is the first joint for being connected with described detection main frame, for the second joint being connected with described cable, and be used for and institute
Stating the 3rd joint that gas turbine starter connects, described detection main frame is provided with power supply, multiple signal lights, gas generator turn
Speed table, free turbine tachoscope, electric starter line voltmeter, exhaust gas thermometer and self-inspection knob.
Preferably, described power supply is the lithium battery of built-in 24v.
Preferably, described first joint of described detection cable, described second joint and described 3rd joint all can make
By circular stitch connected mode, and it is furnished with cap nut screwing clamping.
Preferably, being used in described detection main frame detects minimum lubricating oil pressure signal, the electricity of electric starter disengagement signal
Road uses physical isolation design, described power supply and the relay of 24v, signal indicator is concatenated, relay has two normally opened tactile
Point: one is connected with described power supply, described signal lights, one concatenates with the respective lines of described aircraft control unit.
Preferably, being used in described detection main frame detects gasifier speed and the display of free turbine tach signal
Circuit is provided with signal amplifier.
Preferably, described detection cable is the cable of one-to-many.
A kind of gas turbine starter outfield provided by the utility model running parameter detection device, can check each in situ
Individual electric attachments and the working condition of gas turbine starter, can quickly position gas turbine starter failure cause and position,
Improve outfield troubleshooting efficiency and shorten the troubleshooting cycle.
Accompanying drawing explanation
The following drawings is only intended to, in schematically illustrating this utility model and explaining, not limit model of the present utility model
Enclose.Wherein,
Fig. 1 is a kind of gas turbine starter outfield running parameter inspection according to a specific embodiment of the present utility model
Survey the structural principle schematic diagram of device.
Detailed description of the invention
In order to technical characteristic of the present utility model, purpose and effect are more clearly understood from, now comparison accompanying drawing explanation
Detailed description of the invention of the present utility model.Wherein, identical parts use identical label.
Fig. 1 is a kind of gas turbine starter outfield running parameter inspection according to a specific embodiment of the present utility model
Survey the structural principle schematic diagram of device.Shown in Figure 1, this utility model provides the work of a kind of gas turbine starter outfield
Parameter detection device, it is for the combustion gas whirlpool being connected with aircraft control unit 2 by multiple cables 10 installed aboard
Wheel starter 1 is operated parameter detecting, and it includes detecting main frame 3, detection cable 4, and described detection cable 4 is threeway cable,
Described detection cable 4 is provided with the first joint 41 for being connected with described detection main frame 3, for be connected with described cable 10
Second joint 42, and for the 3rd joint 43 being connected with described gas turbine starter 1, described detection main frame 3 is provided with
Power supply (not shown), multiple signal lights 31, gasifier speed table 32, free turbine tachoscope 33, electrically actuated electromechanics
Source voltmeter 34, exhaust gas thermometer 35 and self-inspection knob 36.
The innovative point of this utility model maximum is, described detection cable 4 is threeway cable, say, that described detection
Main frame 3 can be inserted with the plug of cable 10 and the electric attachments of gas turbine starter 1 being connected to aircraft control unit 2 simultaneously
Seat connects, and the most just can not affect between gas turbine starter 1 and aircraft control unit 2 in the case of signal transmission, will
The running parameter of gas turbine starter 1 and the control signal of aircraft control unit 2 lead to described detection main frame 3 simultaneously, from
And realize obtaining in situ the purpose of gas turbine starter 1 key parameter and control signal.
Described detection cable 4 can be man-to-man cable, only gathers the signal of a described cable 10 i.e. every time, described
Detection cable 4 can also be the cable of one-to-many as shown in Figure 1, gathers described aircraft control unit 2 and described combustion the most simultaneously
The signal of all of described cable 10 between air turbine starter 1.
The described power supply of described detection main frame 3 can be the lithium battery of built-in 24v, so can be without external power supply
Under the conditions of carry out the work.
Described first joint 41 of described detection cable 4, described second joint 42 and described 3rd joint 43 all can make
By circular stitch connected mode, and it is furnished with cap nut screwing clamping, vibrates when so can prevent electromotor from work and come off.
Described signal lights 31 can be used for by the described power supply of described detection main frame 3 to described gas turbine starter 1
Send the control signals such as parking, motor disengagement, slow train, igniting intuitively to show, thus can help and judge described gas turbine
The starter 1 response situation to command adapted thereto.
Described self-inspection knob 36 can by running contact (not shown) respectively with the circuit string of each described signal lights 31
Connection, thus can carry out self-inspection to described signal lights 31 and circuit thereof one by one, it is judged that each circuit whether normal ON, to avoid because setting
Standby faults itself affects breakdown judge.Additionally, also can be given described gas turbine starter 1 respectively by described self-inspection knob 36
The electric attachments such as electromagnetic valve for braking, power set state electromagnetic valve, slow train electromagnetic valve, igniter left-right dots fire coil are powered.
By observing, detect the action situation of the electric attachments such as electromagnetic valve, ignition coil, can realize at described gas turbine starter 1
The most normal purpose of work of electric attachments is checked under static state.
The gas generator that described gasifier speed table 32 collects from described gas turbine starter 1 for display
Rotating speed；The free turbine rotating speed that described free turbine tachoscope 33 collects from described gas turbine starter 1 for display；Institute
State electric starter line voltmeter 34 for showing the electric starter supply voltage collected from described gas turbine starter 1.
For avoiding signal disturbing, for being used for detecting minimum lubricating oil pressure signal in described detection main frame 3, electric starter takes off
The circuit of ON signal can use physical isolation to design, and the described power supply of 24v will concatenate with relay, signal indicator and (do not show in figure
Go out).Two normally opened contacts are had: one is connected with described power supply, described signal lights 31, in order to show that signal indicator is opened on relay
OFF signal；One concatenates with the respective lines of aircraft control unit 2, in order to signal indicator switching signal is truly passed to aircraft control
Unit 2 processed.
Owing to gas generator (Ng) rotating speed and free turbine (Np) tach signal are low voltage signals, therefore in described inspection
Survey and the display circuit in main frame 3 can be provided with signal amplifier amplification, so can ensure the low-voltage frequency in starting process
Can correctly gather and show.
A kind of gas turbine starter outfield provided by the utility model running parameter detection device, can check each in situ
Individual electric attachments and the working condition of gas turbine starter, can quickly position gas turbine starter failure cause and position,
Improve outfield troubleshooting efficiency and shorten the troubleshooting cycle.
Although it will be appreciated by those skilled in the art that this utility model is to be described according to the mode of multiple embodiments
, but the most each embodiment only comprises an independent technical scheme.In description, so narration is only used to clear
For the sake of, description should be understood by those skilled in the art as an entirety, and by skill involved in each embodiment
Art scheme is regarded as and can be understood protection domain of the present utility model in the way of being mutually combined into different embodiment.
The foregoing is only the schematic detailed description of the invention of this utility model, be not limited to model of the present utility model
Enclose.Any those skilled in the art, the equivalent variations made on the premise of without departing from design of the present utility model and principle,
Amendment and combination, all should belong to the scope of this utility model protection.
Claims (6)
1. gas turbine starter outfield running parameter detection a device, its for install aboard by multiple electricity
The gas turbine starter that cable is connected with aircraft control unit is operated parameter detecting, it is characterised in that it includes that detection is main
Machine, detection cable, described detection cable is threeway cable, and described detection cable is provided with for being connected with described detection main frame
First joint, for the second joint being connected with described cable, and is used for the 3rd be connected with described gas turbine starter
Joint, described detection main frame is provided with power supply, multiple signal lights, gasifier speed table, free turbine tachoscope, electrically actuated
Electromechanical source voltmeter, exhaust gas thermometer and self-inspection knob.
Gas turbine starter outfield the most according to claim 1 running parameter detection device, it is characterised in that described electricity
Source is the lithium battery of built-in 24v.
Gas turbine starter outfield the most according to claim 1 running parameter detection device, it is characterised in that described inspection
Survey described first joint of cable, described second joint and described 3rd joint and all use circular stitch connected mode, and
It is furnished with cap nut screwing clamping.
Gas turbine starter outfield the most according to claim 2 running parameter detection device, it is characterised in that described inspection
Survey the circuit employing physical isolation design for detecting minimum lubricating oil pressure signal, electric starter disengagement signal in main frame, will
The described power supply of 24v concatenates with relay, signal indicator, and relay has two normally opened contacts: one with described power supply, described
Signal lights connects, and one concatenates with the respective lines of described aircraft control unit.
Gas turbine starter outfield the most according to claim 1 running parameter detection device, it is characterised in that described inspection
The signal that is provided with in the display circuit detecting gasifier speed and free turbine tach signal surveyed in main frame amplifies
Device.
Gas turbine starter outfield the most according to claim 1 running parameter detection device, it is characterised in that described inspection
Survey the cable that cable is one-to-many.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620648927.0U CN205841014U (en) | 2016-06-28 | 2016-06-28 | A kind of gas turbine starter outfield running parameter detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620648927.0U CN205841014U (en) | 2016-06-28 | 2016-06-28 | A kind of gas turbine starter outfield running parameter detection device |
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| Publication Number | Publication Date |
|---|---|
| CN205841014U true CN205841014U (en) | 2016-12-28 |
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| CN201620648927.0U Active CN205841014U (en) | 2016-06-28 | 2016-06-28 | A kind of gas turbine starter outfield running parameter detection device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109358593A (en) * | 2018-09-11 | 2019-02-19 | 陕西千山航空电子有限责任公司 | A kind of portable aviation EDPAC Engine Diagnostic Package |
| CN111693292A (en) * | 2020-06-16 | 2020-09-22 | 成都航利航空科技有限责任公司 | Detection system and method for engine gas turbine starter |
| CN112525253A (en) * | 2020-11-03 | 2021-03-19 | 哈尔滨哈飞航空工业有限责任公司 | External field in-situ test system and test method of integrity and use monitoring system |
-
2016
- 2016-06-28 CN CN201620648927.0U patent/CN205841014U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109358593A (en) * | 2018-09-11 | 2019-02-19 | 陕西千山航空电子有限责任公司 | A kind of portable aviation EDPAC Engine Diagnostic Package |
| CN111693292A (en) * | 2020-06-16 | 2020-09-22 | 成都航利航空科技有限责任公司 | Detection system and method for engine gas turbine starter |
| CN112525253A (en) * | 2020-11-03 | 2021-03-19 | 哈尔滨哈飞航空工业有限责任公司 | External field in-situ test system and test method of integrity and use monitoring system |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |