CN108061656A - A kind of method for checking aero-engine novel integrated electronic controller - Google Patents
A kind of method for checking aero-engine novel integrated electronic controller Download PDFInfo
- Publication number
- CN108061656A CN108061656A CN201711320806.9A CN201711320806A CN108061656A CN 108061656 A CN108061656 A CN 108061656A CN 201711320806 A CN201711320806 A CN 201711320806A CN 108061656 A CN108061656 A CN 108061656A
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- Prior art keywords
- engine
- electronic controller
- signal
- aero
- novel integrated
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
Abstract
The present invention provides a kind of method for checking aero-engine novel integrated electronic controller, is related to aero-engine technology field.A kind of method for checking aero-engine novel integrated electronic controller, the difference of prototype integrated full electric propulsion and novel integrated electronic controller is determined first, further according to the relevant parameter of difference modification import ground check platform, independent check finally is carried out to novel integrated electronic controller using amended ground check platform.The method provided by the invention for checking aero-engine novel integrated electronic controller, independent check is carried out to novel integrated electronic controller by the relevant parameter for changing import ground check platform, failure and security risk can be found before on-line retrieval, greatly reduces the time of aero-engine on-line retrieval.
Description
Technical field
The present invention relates to aero-engine technology field more particularly to a kind of inspection aero-engine novel integrated electronics tune
The method for saving device.
Background technology
Control device of the integrated full electric propulsion (referred to as comprehensive tune) as aero-engine, it is past being gone to engine test
Independent check is carried out, main contents include：Inspection and adjusting to integrated full electric propulsion setting value adjust integrated electronics
The measurement of device and the inspection of control function and adjusting.After independent check is complete, integrated full electric propulsion could be in test run link to boat
Empty engine implements effective control according to predetermined scheme.Integrated full electric propulsion directly appear on the stage without independent check into
Row on-line retrieval can not only extend the time for making aero-engine on-line retrieval, and can adjust faulty integrated electronics
Device is appeared on the stage test run, is lost time, man power and material, is delayed production.
Ground check platform can realize to integrated full electric propulsion carry out independent check, but existing ground check platform be into
Mouth ground check platform can only check the prototype integrated full electric propulsion applied to import prototype engine of import, and can not be real
Now applied to Domestic New the novel integrated electronic controller of motivation is started to check domestic.
The content of the invention
The defects of for the prior art, the present invention provide a kind of side for checking aero-engine novel integrated electronic controller
Method is realized and domestic novel integrated electronic controller is checked.
In order to solve the above technical problems, the technical solution used in the present invention is：A kind of inspection aero-engine is new comprehensive
The method for closing electronic controller, this method is realized based on import ground check platform, is comprised the following steps：
Step 1, the difference for determining novel integrated electronic controller and prototype integrated full electric propulsion, particular content are：
(1) novel integrated electronic controller need not control the turbine cooling system of aero-engine, and prototype
Integrated full electric propulsion needs to control the turbine cooling system of aero-engine；
(2) novel integrated electronic controller controls the discrete magnitude signal that new work engine needs signal during repairing to be B%,
And prototype integrated full electric propulsion control prototype engine needs the discrete magnitude signal that signal during repairing is A%；
(3) the discrete magnitude output signal of rotating speed when novel integrated electronic controller is used to that the starter of engine to be controlled to exit
For D%, and the discrete magnitude output signal of rotating speed is when prototype integrated full electric propulsion is used to that the starter of engine to be controlled to exit
C%；
(4) novel integrated electronic controller does not have non-cooled signal, and prototype integrated full electric propulsion has non-cooled signal；
(5) novel integrated electronic controller is different from the afterburner ignition mode of prototype integrated full electric propulsion：Novel integrated
The afterburner ignition executing agency of electronic controller continuous firing M seconds, prototype integrated full electric propulsion afterburner ignition executing agency are N
Subpulse signal；
(6) boat that the aero-engine and prototype integrated full electric propulsion that novel integrated electronic controller is controlled are controlled
Maximum limits value processed and minimum alarm limits value, the maximum rating of alarming of vibration alarming value limits value, the lubricating oil pressure of empty engine
Low pressure rotating speed limits value N1, maximum rating high pressure rotating speed limits value N2With the temperature limit value T of maximum rating4It is different；
Step 2, the difference for novel integrated electronic controller and prototype integrated full electric propulsion change the inspection of import ground
The parameter setting of platform is looked into, particular content is：
(1) the turbine cooling control section in import ground check platform is removed；
(2) discrete magnitude signal for being B% by the signal definition for controlling engine repairing of import ground check platform；
(3) the turbine cooling solenoid signal of import ground check platform is defined as that the starter of engine is controlled to move back
The discrete magnitude that the output signal of rotating speed is D% when going out；
(4) by the E% on the non-cooled modification of signal of import ground check platform engine skyborne starting opportunity in order to control
Discrete magnitude；
(5) the afterburner ignition n times pulse signal of import ground check platform is revised as a persistent signal, the time is M seconds；
Step 3, the inspection procedure specification according to import ground check platform use the import ground check platform pair of Reparametrization
Novel integrated electronic controller carries out independent check；
In the result of inspection, the aero-engine rotating speed shown by the import ground check platform of Reparametrization, which is multiplied by, is
Number M/N is the actual revolution of aero-engine, wherein, M reaches corresponding speed probe when 100% for prototype engine rotating speed
Output valve, N are the output valve that new work engine rotating speed reaches corresponding speed probe when 100%.
As shown from the above technical solution, the beneficial effects of the present invention are：A kind of inspection aeroplane engine provided by the invention
The method of machine novel integrated electronic controller by changing the parameter setting of existing ground check platform, is realized to novel integrated electricity
The independent check of sub- adjuster, greatly reduces workload, reduces labor intensity, improves production efficiency, ensures that test run is suitable
Profit carries out.
Description of the drawings
Fig. 1 is to be examined in import ground check platform provided in an embodiment of the present invention for detecting the ground of integrated full electric propulsion
Look into the part-structure schematic diagram of platform A；
Fig. 2 is the ground check platform for being used to simulate aero-engine in import ground check platform provided in an embodiment of the present invention
The part-structure schematic diagram of B；
Fig. 3 is the part-structure schematic diagram of the ground check platform A of Reparametrization provided in an embodiment of the present invention；
Fig. 4 is the part-structure schematic diagram of the ground check platform B of Reparametrization provided in an embodiment of the present invention.
Specific embodiment
With reference to the accompanying drawings and examples, the specific embodiment of the present invention is described in further detail.Implement below
Example is not limited to the scope of the present invention for illustrating the present invention.
The present embodiment is using domestic integrated full electric propulsion used in certain factory's aero-engine as novel integrated electrical adjustment
Device on the basis of certain model import ground check platform A as depicted in figs. 1 and 2 and ground check platform B, uses present invention side
Method is realized to the novel integrated electronic controller in online preceding carry out independent check.
A kind of method for checking aero-engine novel integrated electronic controller, this method are based on import ground check platform A
It realizes, comprises the following steps with B：
Step 1, the difference for determining novel integrated electronic controller and prototype integrated full electric propulsion, particular content are：
(1) novel integrated electronic controller need not control the turbine cooling system of aero-engine, and prototype
Integrated full electric propulsion needs to control the turbine cooling system of aero-engine；
(2) novel integrated electronic controller controls the discrete magnitude signal that new work engine needs signal during repairing to be B%,
And prototype integrated full electric propulsion control prototype engine needs the discrete magnitude signal that signal during repairing is A%；
(3) the discrete magnitude output signal of rotating speed when novel integrated electronic controller is used to that the starter of engine to be controlled to exit
For D%, and the discrete magnitude output signal of rotating speed is when prototype integrated full electric propulsion is used to that the starter of engine to be controlled to exit
C%；
(4) novel integrated electronic controller does not have non-cooled signal, and prototype integrated full electric propulsion has non-cooled signal；
(5) novel integrated electronic controller is different from the afterburner ignition mode of prototype integrated full electric propulsion：Novel integrated
The afterburner ignition executing agency of electronic controller continuous firing M seconds, prototype integrated full electric propulsion afterburner ignition executing agency are N
Subpulse signal；
(6) boat that the aero-engine and prototype integrated full electric propulsion that novel integrated electronic controller is controlled are controlled
Maximum limits value processed and minimum alarm limits value, the maximum low pressure of alarming of vibration alarming value limits value, the lubricating oil pressure of empty engine
Rotating speed limits value N1, maximum high-voltage rotating speed limits value N2With temperature limit value T4It is different；
Step 2, the difference for novel integrated electronic controller and prototype integrated full electric propulsion change the inspection of import ground
The parameter setting of platform is looked into, particular content is：
(1) the turbine cooling control section in import ground check platform is removed；
(2) the engine fuel control signal of import ground check platform is defined as to the discrete magnitude signal of B%；
(3) the turbine cooling solenoid signal of import ground check platform is defined as that the starter of engine is controlled to move back
The discrete magnitude that the output signal of rotating speed is D% when going out；
(4) by the E% on the non-cooled modification of signal of import ground check platform engine skyborne starting opportunity in order to control
Discrete magnitude；
(5) the afterburner ignition n times pulse signal of import ground check platform is revised as a persistent signal, the time is M seconds；
Step 3, the inspection procedure specification according to import ground check platform use the import ground check platform pair of Reparametrization
Novel integrated electronic controller carries out independent check；
In the result of inspection, the aero-engine rotating speed shown by the import ground check platform of Reparametrization, which is multiplied by, is
Number M/N is the actual revolution of aero-engine, wherein, M reaches corresponding speed probe when 100% for prototype engine rotating speed
Output valve, N are the output valve that new work engine rotating speed reaches corresponding speed probe when 100%.
In the present embodiment, the ground check platform B using Reparametrization as shown in Figure 4 replaces engine as excitation
Device sends signal, the letter that novel integrated electronic controller is sent as feedback according to engine to novel integrated electronic controller
Number confirm engine condition, then send series of instructions to engine implement effectively control.Novel integrated electronic controller is sent out
The instruction gone out carries out display monitoring by the ground check platform A of Reparametrization as shown in Figure 3, judges novel integrated electronics tune
Whether section device can coordinate engine test.
In the present embodiment, prototype integrated full electric propulsion be used for control prototype engine repairing when signal be 15% from
Amount signal is dissipated, novel integrated electronic controller is used to control the discrete magnitude signal that signal during new work engine repairing is 17%,
The discrete magnitude that the output signal of rotating speed is 53% when prototype integrated full electric propulsion is used to that the starter of engine to be controlled to exit, newly
The discrete magnitude that the output signal of rotating speed is 63% when pattern synthesis electronic controller is used to that the starter of engine to be controlled to exit, it is new
Integrated full electric propulsion controls engine skyborne starting opportunity using 61% discrete magnitude, novel integrated electronic controller
Afterburner ignition executing agency continuous working period is 3 seconds.
Finally it should be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
The present invention is described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that：It still may be used
Either which part or all technical characteristic are equal with modifying to the technical solution recorded in previous embodiment
It replaces；And these modifications or replacement, the essence of appropriate technical solution is not made to depart from the model that the claims in the present invention are limited
It encloses.
Claims (1)
- A kind of 1. method for checking aero-engine novel integrated electronic controller, it is characterised in that：Comprise the following steps：Step 1, the difference for determining novel integrated electronic controller and prototype integrated full electric propulsion, particular content are：(1) novel integrated electronic controller need not control the turbine cooling system of aero-engine, and prototype integrates Electronic controller needs to control the turbine cooling system of aero-engine；(2) novel integrated electronic controller controls the discrete magnitude signal that new work engine needs signal during repairing to be B%, and former Pattern synthesis electronic controller control prototype engine needs the discrete magnitude signal that signal during repairing is A%；(3) the discrete magnitude output signal of rotating speed is when novel integrated electronic controller is used to that the starter of engine to be controlled to exit D%, and discrete magnitude output signal of the prototype integrated full electric propulsion for rotating speed when the starter of engine being controlled to exit is C%；(4) novel integrated electronic controller does not have non-cooled signal, and prototype integrated full electric propulsion has non-cooled signal；(5) novel integrated electronic controller is different from the afterburner ignition mode of prototype integrated full electric propulsion：Novel integrated electronics The afterburner ignition executing agency of adjuster continuous firing M seconds, prototype integrated full electric propulsion afterburner ignition executing agency are n times arteries and veins Rush signal；(6) the aviation hair that the aero-engine and prototype integrated full electric propulsion that novel integrated electronic controller is controlled are controlled The vibration alarming value limits value of motivation, lubricating oil pressure be maximum alarm limits value processed and minimum alarm limits value, maximum rating it is low Press rotating speed limits value N1, maximum rating high pressure rotating speed limits value N2With the temperature limit value T of maximum rating4It is different；Step 2, the difference for novel integrated electronic controller and prototype integrated full electric propulsion, change import ground check platform Parameter setting, particular content is：(1) the turbine cooling control section in import ground check platform is removed；(2) discrete magnitude signal for being B% by the signal definition for controlling engine repairing of import ground check platform；(3) when the turbine cooling solenoid signal of import ground check platform being defined as that the starter of engine is controlled to exit The discrete magnitude that the output signal of rotating speed is D%；(4) by the non-cooled modification of signal of import ground check platform in order to control the E% on engine skyborne starting opportunity from Dissipate amount；(5) the afterburner ignition n times pulse signal of import ground check platform is revised as a persistent signal, the time is M seconds；Step 3, the inspection procedure specification according to import ground check platform, using the import ground check platform of Reparametrization to new Integrated full electric propulsion carries out independent check；In the result of inspection, the aero-engine rotating speed shown by the import ground check platform of Reparametrization is multiplied by coefficient M/ N is the actual revolution of aero-engine, wherein, M is the output that prototype engine rotating speed reaches corresponding speed probe when 100% Value, N are the output valve that new work engine rotating speed reaches corresponding speed probe when 100%.
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Cited By (4)
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| CN108872836A (en) * | 2018-07-09 | 2018-11-23 | 深圳市合信达控制系统有限公司 | A kind of detection method and device of control panel anti-electromagnetic-radiation ability |
| CN109556870A (en) * | 2018-11-29 | 2019-04-02 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aeroengine thrust augmentation connects the troubleshooting inspection method of failure |
| CN111208797A (en) * | 2019-12-20 | 2020-05-29 | 四川大学 | Integrated tester for electronic regulator of aircraft aeroengine |
| CN112229636A (en) * | 2020-09-21 | 2021-01-15 | 成都国营锦江机器厂 | Debugging system based on electronic regulator |
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| CN111208797A (en) * | 2019-12-20 | 2020-05-29 | 四川大学 | Integrated tester for electronic regulator of aircraft aeroengine |
| CN112229636A (en) * | 2020-09-21 | 2021-01-15 | 成都国营锦江机器厂 | Debugging system based on electronic regulator |
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Application publication date: 20180522 |