CN110231184A - A kind of Core Engine cabin fire full-scale trial device - Google Patents
A kind of Core Engine cabin fire full-scale trial device Download PDFInfo
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- CN110231184A CN110231184A CN201810199312.8A CN201810199312A CN110231184A CN 110231184 A CN110231184 A CN 110231184A CN 201810199312 A CN201810199312 A CN 201810199312A CN 110231184 A CN110231184 A CN 110231184A
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- 238000000034 method Methods 0.000 claims abstract description 14
- 238000013461 design Methods 0.000 claims abstract description 13
- 230000001535 kindling effect Effects 0.000 claims abstract description 12
- 238000004088 simulation Methods 0.000 claims abstract description 6
- 238000012360 testing method Methods 0.000 claims description 50
- 238000010438 heat treatment Methods 0.000 claims description 22
- 239000003921 oil Substances 0.000 claims description 13
- 238000005259 measurement Methods 0.000 claims description 9
- 239000007788 liquid Substances 0.000 claims description 8
- 239000010687 lubricating oil Substances 0.000 claims description 8
- 238000009423 ventilation Methods 0.000 claims description 8
- 239000000295 fuel oil Substances 0.000 claims description 4
- 238000009826 distribution Methods 0.000 claims description 3
- 239000003595 mist Substances 0.000 claims description 2
- 238000004079 fireproofing Methods 0.000 abstract description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 5
- 238000005507 spraying Methods 0.000 description 5
- 239000003990 capacitor Substances 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 230000000977 initiatory effect Effects 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000001354 calcination Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005485 electric heating Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000010761 intermediate fuel oil Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 241000521257 Hydrops Species 0.000 description 1
- 206010030113 Oedema Diseases 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000003517 fume Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen group Chemical group [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000005619 thermoelectricity Effects 0.000 description 1
- 238000001757 thermogravimetry curve Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention belongs to aero-engine fireproofing technique fields, construct a kind of Core Engine cabin fire full-scale trial device, the typical condition condition of practical cabin can be simulated, the more really kindling and fire spread in reflection core cabin, provides basic data for Core Engine cabin fire protection design and analogue simulation.
Description
Technical field:
The invention belongs to aero-engine fireproofing technique fields, construct a kind of Core Engine cabin fire full size
Experimental rig can simulate the typical condition condition of practical cabin, more the really kindling and fire spread in reflection core cabin,
Basic data is provided for Core Engine cabin fire protection design and analogue simulation.
Background technique:
In each flame range of civil aircraft, throughout complicated pipeline in aircraft engine core cabin, and whole area in cabin
Domain temperature is relatively high, is one of the significant risk position for causing aircraft to catch fire, flameproof protection to the safe operation of aircraft extremely
It closes important.US Federal Aviation Administration (FAA) and Civil Aviation Administration of China (CAAC) are all anti-to civil aircraft engine core cabin
Fire design proposes relevant airworthiness requirement (FAR33.17 and CAAR33.17), from material, structure, design layout etc.
Fire line proposes strict requirements.
US Federal Aviation Administration's Advisory Circulars (AC33.17-1A) further illustrate civil aircraft engine core cabin
The technical detail of fire protection design, and airworthiness compliance method is given with regard to the Fire Test of material, component and structure.Special attention will be given to
The ignition condition of the venting practice of prevention kindling and overheat in flame range, high temperature surface and spontaneous combustion etc., and prevent fires and try in component
Flame impingement method for determining position etc. when testing.And specific engine room structure characteristic must be taken into consideration to determine and close in the design in terms of these
The baked wheaten cake scene of reason, this just needs to be grasped the basic law of machinery space fire kindling, burning and heat transfer.
On the other hand, since aircraft engine core cabin internal structure is sufficiently complex, local environment is also very special, existing
Our shortages of stage are caught fire to it and the quantitative recognition of fire spread rule, this directly results in the fire prevention of civil aircraft enging cabin and sets
The real machine test that places one's entire reliance upon is counted, but not only the period is long for real machine test, it is expensive, especially in the design typification rank of engine
Section can fire development to enging cabin and fire prevention there is an urgent need to establish a set of reliable and effective analysis method and calculating instrument
System effectiveness carries out the assessment of safe and reasonable, shortens the lead time.
Currently, the simulation experiment method for generalling use diminution scale model or simplified cabin both at home and abroad is studied.But
Core cabin test model in existing testing stand does not establish all geometrical characteristics fully according to practical cabin, but logical
The risk for crossing the kindling and fire spread in analysis cabin, summarizes the feature structure for influencing enging cabin fire development, will be complicated
Pipeline and attachment modelling be standard feature object.Although this simplifies test and constitutes, the repeatability of test result is improved,
It is that there are larger gaps with practical cabin, cannot really reflects the kindling and fire spread of core cabin.
Summary of the invention:
A kind of aircraft engine nacelle typical case fire test platform system, it is characterised in that: modular design method is used, whole
A core cabin full-scale trial platform is divided into seven big modules, respectively test container and safety protection module, 1: 1 cabin geometry
Model and support stand module, entrance Ventilation Control module, wall surface heating module, fire source module, ignition module and data acquisition
Module.It is the testing stand safe operation, easy to use, experimental data can be accumulated, summarizes and burns scene, is Core Engine
Cabin fire protection design and analogue simulation provide basic data.
A kind of aircraft engine nacelle typical case fire test platform system, it is characterised in that: 1: 1 engine core cabin of foundation
Testing stand, can measure the crucial fire parameter distribution such as temperature field, heat flow field, flame forms simultaneously, and system sampling frequency is not low
In 10Hz, measurement point is no less than 96.
A kind of aircraft engine nacelle typical case fire test platform system, it is characterised in that: 1: 1 engine core cabin of foundation
Testing stand can carry out three kinds of fuel oil, lubricating oil and cable combustible fire tests, can simulate mist of oil fire, liquid pool fire, high temperature
Typical fire type in the cores cabin such as surface kindling and cable kindling.
A kind of aircraft engine nacelle typical case fire test platform system, it is characterised in that: 1: 1 enging cabin core engine of foundation
Cabin testing stand can simulate the flow characteristics of typical entrance ventilation condition in cabin, wall surface temperature condition and engine room inside.
Detailed description of the invention:
Fig. 1 is aircraft engine nacelle typical case fire test platform internal system structure chart, wherein 1 is camera；2 be a fire control
Device processed；3 be frequency converter；4 be heating controller；5 be power cabinet；6 be network cabinet；7 be oil feed pump；8 be air-supply turbofan；9 be to send
Air piping；10 be engine test cabin；11 be camera；12 be camera；13 be vasculum；14 hang for row；15 be camera shooting
Head；16 be vasculum；17 be display；18 be control room；19 be main laboratory；20 be fume collecting chamber；21 be the area D heater；22
For the area C heater；23 be the area B heater；24 be the area A heater；25 core cabin areas；26 be atomizer；27 be fire rod；28
For oil sump A；29 be oil sump B；30 be oil sump C；31 be oil sump D；32 be inside cable.
Fig. 2 is aircraft engine heater body structure chart, wherein 21 be the area D heater；22 be the area C heater；23 be B
Area's heater；24 be the area A heater；25 be core cabin area.
Fig. 3 is respectively the inside of aircraft engine internal simulation oil flame, liquid pool fire, cable fire and overall diagram from left to right
Structure chart.Wherein 25 core cabin area；26 be atomizer；27 be fire rod；28 be oil sump A；29 be oil sump B；30 be oil sump C；
31 be oil sump D；32 be inside cable.
Fig. 4 is the flow chart of aircraft engine nacelle typical case fire test platform system.
Fig. 5 is the structural map of aircraft engine nacelle typical case fire test platform system.
Specific embodiment:
Solution of the invention is: using modular design method, entire core cabin full-scale trial platform is divided into
Seven big modules, respectively test container and safety protection module, 1: 1 cabin geometrical model and support stand module, entrance are logical
Wind control module, wall surface heating module, fire source module, ignition module and data acquisition module.
Preferably, the steel construction container that the test container bulk is * 5m high * 4 meters of 12m long wide.Consider this
The safety of secondary test process is mounted with fire hydrant outside test container, is provided with CO2 self-extinguishing equipment in container
And hand extinguisher, for testing the emergency action of emergency situations, it is ensured that the safety of testing crew.
Preferably, the test cabin geometrical model is constructed referring to certain model engine 1: 1.Since practical engine room inside is deposited
There are the affiliated facilities such as sufficiently complex pipeline, route and air hose, according to these pipeline facilities relative to the flowing shadow in cabin
Sound has been done shown in preliminary simplification.Engine room model is constituted using the steel plate sectional of 5mm thickness.In view of high temperature of fire meeting during test
Cause cabin to deform, is considered according to 1 with 1 appendix to possible high temperature section component is tested.Engine room model is fixed on the liquid flexibly gone up and down
On flattening bench.
Preferably, the entrance Ventilation Control module designs according to certain model engine nacelle and provides parameter, core cabin
Entrance ventilation condition are as follows: inlet temperature 287K-466K, inlet pressure 35.93-150kPa, inlet flow rate 0.16-0.64kg/s,
Inlet oxygen concentration 17.5%-20.9%.Inlet air flow is entered by 6 ventilation holes that cabin head is circumferentially evenly arranged
In cabin.To simulate above-mentioned ventilation condition, realized using distribution (air is mixed with nitrogen) system.Primary air is air, by sky
Air compressor generates, and proportion air-flow is nitrogen, by changing the proportion of degree of nitrogen, adjusts inlet oxygen concentration.Mixed gas it is total
Flow is accurately controlled by mass flowmenter.Mixed gas temperature is controlled by inlet gas heating device.
Preferably, the wall surface heating module considers that main high-temperature wall surface is the combustion chamber of inner surface in practical cabin
Surface 800-1000K, high-pressure unit section surface 650-850K and high temperature air hose 600-800K.These high temperature surfaces are not only a little
Fire source also will affect fire development process.Since this wall surface heating temperature is high, no more than 400 DEG C of common electric heating tube, because
This selects ceramet plate resistant to high temperature.The ceramic electroheating tube can be heated to 1000 DEG C.In order to control the heating range of wall surface,
Testing stand is realized using automatic heating device control system.The high-pressure section and low-pressure section of the device are independent from each other two
Control system is mainly made of heater, temperature measuring section and control cabinet, and wherein control cabinet mainly includes power unit, intelligence
It can temperature controller, alarm portion, cooling segment, indicating section, clocking portions, error protection part and control switch part.Equipment
After energization, power supply indicator is bright, carries out parameter setting to adjuster and timer as requested later；Press heating starting by
Button, heating lamp is bright, and heater is started to work；When temperature reaches the lower limit of operating temperature for the first time, timer starts timing；
When temperature reaches the upper limit of operating temperature, system issues instruction, and heater stops heating；When temperature drops to lowest temperature,
System will issue heating instructions, and heater automatically continues heating；Repeatedly；Timer reaches the setting time, stops heating tube
Work, and issue alarm signal；When pressing heating stop button, heating lamp goes out, and heater stops heating；The process of heating
In, if heating temperature is more than temperature upper limit, system can be automatically stopped heating, and issue sound and light alarm signal；System is equipped with emergency stop
Button in case of emergency presses emergency stop button, and system will cut off heating power supply, it is ensured that safety.
Preferably, the fire source module considers typical three kinds of combustibles, respectively fuel oil, lubricating oil and line in cabin
Cable.Its intermediate fuel oil and lubricating oil are divided into spraying fire and liquid pool fire according to kindling form again.
The different working condition of pipeline can be divided into stable state and continue that spraying and transient state is limited to be sprayed two kinds after being caught fire according to cabin
Operating condition.
It for fuel pipe, after fire occurs, will be cut off immediately for solenoid, therefore subsequent pipeline is when limited
Interior decompression leakage is spraying；For lubricating oil pipeline, after fire occurs, lubricating oil pipeline will maintain normal operating conditions, because
This its leakage spray process continues by spraying close to stable state, i.e., loine pressure remains unchanged in spray process.Both are different
Spray pattern, testing stand are realized automatically by oil path control unit.It tests moderate heat source size (spray amount) and passes through apolegamy appropriate flow
The fuel nozzle of coefficient of discharge is realized.
Liquid pool fire is after simulating pipeline rupture, and fuel oil or lubricating oil hydrops form the product of certain area in the bottom surface of engine
Liquid.This project simulates liquid pool fire using the food tray of fixed-area, and fire size is determined by control food tray area.
A large amount of cables are also disposed in enging cabin, once tired, also very easy initiation fire.It is caught fire according to cable
Mode can be divided into fire caused by the interior fires and external calcination of short circuit initiation.Both modes exist on ignition condition
Very big difference needs to be simulated respectively.For cable fire caused by external calcination, using spraying fire directly burning cable side
Formula is realized.For cable inner short-circuit fire, using the resistive heater in cable, short-circuit fire is simulated by Electric heating
Preferably, the ignition module considers that in engine nacelle, there are three types of main ignition modes, respectively high
Warm surface ignition, point spark initiation and wire short-circuiting are on fire.In these three modes, in high temperature surface ignition and wire short-circuiting belong to
Cause, electric spark ignite as external cause.
The ignition energy for considering that test intermediate fuel oil and lubricating oil kindling need differs greatly, and this project is filled using high-energy ignition
It sets.The device is made of high-energy igniter, high-voltage ignition cable and burning torch.High-energy igniter device passes through boosting rectifying conversion
At DC pulse electric current, charge to energy storage capacitor.Its working principle is that input AC power frequency 220V, by boosting rectifying conversion at
DC pulse electric current charges to energy storage capacitor.When capacitor is full of, discharge current is through discharge tube, choke coil, high-tension shielding electricity
Cable is transmitted to burning torch semiconductor discharge plug, forms high energy arc spark.Residue when igniter stops working, on capacitor
Charge is released by bleeder resistance.
Preferably, the data acquisition module, requires according to test measurement, and testing stand needs to acquire fire parameter and includes:
Temperature (the mild fire scene temperature of inside and outside wall), hot-fluid, air-flow velocity and flame forms.
K-type thermocouple is selected in temperature measurement, and temperature-measuring range is 0-1200 DEG C.Flame and high-temperature flue-gas are measured using straight
Diameter is the K-type thermocouple of 1.5mm, measures the use K-type veneer thermocouple measurement of cabin internal surface temperature.In test, thermoelectricity
It is even to be evenly arranged 8 in the circumferential, totally 24 on same section (surfaces externally and internally 8 each, air 8), 4 measurements are set altogether
Section, totally 96.
Embedded micro heat-flow meter, measurement range 0-100kW/m2 are selected in heat-flow measurement.Heat-flow meter is embedded in cabin
On surfaces externally and internally.In test, heat-flow meter is evenly arranged 4 in the circumferential, totally 8 (each 4 of surfaces externally and internally) on same section, altogether
3 Measure sections are set, totally 24.
Air-flow velocity measurement uses miniature hot-wire anemometer, and measurement range 0-50m/s pops one's head in 20-70 DEG C of operating temperature.
This project select hot line probe it is very small and exquisite, substantially will not stream field impact.In test, wind speed probe is in inlet induction
The same section in road is circumferentially upper uniformly to visit arrangement 3, totally 3.
Far infrared glass resistant to high temperature (transmission range: 0.7--14um far infrared) form is set in cabin as flame
The range estimation of form and videograph.Using visible and infrared two-band infrared thermal imagery recorder.The temperature test of the recorder
Range is -40 DEG C~+2000 DEG C, while obtaining Infrared Thermogram and the infrared 640*480 pixel of visible video, it is seen that video 500
Ten thousand pixels.
The above description is only a preferred embodiment of the present invention, is not intended to restrict the invention, for those skilled in the art
For member, the invention may be variously modified and varied.All within the spirits and principles of the present invention, it is made it is any modification,
Equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (4)
1. a kind of aircraft engine nacelle typical case fire test platform system, it is characterised in that: modular design method is used, entire
Core cabin full-scale trial platform is divided into seven big modules, respectively test container and safety protection module, 1: 1 cabin geometry mould
Type and support stand module, entrance Ventilation Control module, wall surface heating module, fire source module, ignition module and data acquisition module
Block.It is the testing stand safe operation, easy to use, experimental data can be accumulated, summarizes and burns scene, is Core Engine cabin
Fire protection design and analogue simulation provide basic data.
2. aircraft engine nacelle typical case fire test platform system according to claim 1, it is characterised in that: the 1: 1 of foundation
Engine core cabin testing stand can measure the crucial fire parameter distribution such as temperature field, heat flow field, flame forms simultaneously, be
Sample frequency of uniting is not less than 10Hz, and measurement point is no less than 96.
3. aircraft engine nacelle typical case fire test platform system according to claim 1, it is characterised in that: the 1: 1 of foundation
Engine core cabin testing stand can carry out three kinds of fuel oil, lubricating oil and cable combustible fire tests, can simulate mist of oil
Typical fire type in the cores cabins such as fire, liquid pool fire, the kindling of high temperature surface and cable kindling.
4. aircraft engine nacelle typical case fire test platform system according to claim 1, it is characterised in that: the 1: 1 of foundation
Enging cabin core cabin testing stand can simulate typical entrance ventilation condition, wall surface temperature condition and cabin in cabin
Internal flow characteristics.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810199312.8A CN110231184A (en) | 2018-03-05 | 2018-03-05 | A kind of Core Engine cabin fire full-scale trial device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810199312.8A CN110231184A (en) | 2018-03-05 | 2018-03-05 | A kind of Core Engine cabin fire full-scale trial device |
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| CN110231184A true CN110231184A (en) | 2019-09-13 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110619778A (en) * | 2019-09-30 | 2019-12-27 | 中国民航大学 | Fire-fighting training simulation and evaluation system for aircraft engine |
| CN111238820A (en) * | 2020-03-25 | 2020-06-05 | 中国航发哈尔滨东安发动机有限公司 | Lubricating oil pump fire-proof test equipment |
| CN111681520A (en) * | 2020-06-11 | 2020-09-18 | 清华大学 | Simulation experiment device for external fire of airplane |
| CN112733249A (en) * | 2019-10-11 | 2021-04-30 | 中国航发商用航空发动机有限责任公司 | Calculation method and analysis method for typical fire of aircraft engine |
| CN114852369A (en) * | 2022-07-11 | 2022-08-05 | 中国飞机强度研究所 | Heating adjustment control method for high-temperature heat strength test of aircraft nose cone structure |
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