CN106959213A - A kind of method for removing of fanjet afterburner ignition failure - Google Patents
A kind of method for removing of fanjet afterburner ignition failure Download PDFInfo
- Publication number
- CN106959213A CN106959213A CN201710396115.0A CN201710396115A CN106959213A CN 106959213 A CN106959213 A CN 106959213A CN 201710396115 A CN201710396115 A CN 201710396115A CN 106959213 A CN106959213 A CN 106959213A
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- China
- Prior art keywords
- fuel
- afterburner
- flow
- ignition
- oil
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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
- G01M15/04—Testing internal-combustion engines
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
The invention discloses a kind of method for removing of fanjet afterburner ignition failure, particular content is as follows：Fuel manifold is obtained by the analysis to afterburner system operation principle and starts influence of the flow of fuel feeding to igniting；The afterburner system includes Afterburning condition and not Afterburning condition；Catalytic site firearm and fuel manifold component are carried out flow and practiced shooting to test, influence of the flow angle to igniting in fuel jet area is obtained.The present invention is tested by the way that catalytic site firearm and fuel manifold component are carried out flow and practiced shooting, fuel manifold component flow can be obtained excessive, the efficiency of seed region is influenceed, remaining oxygen is lacked due to great rich oil in booster zone, oil-gas ratio is mismatched and is caused afterburner ignition to fail；This method is verified through testing and installing, and ignition failure is excluded.
Description
Technical field
The present invention relates to a kind of failure discharge method, specifically a kind of exclusion side of fanjet afterburner ignition failure
Method.
Background technology
In over one hundred engine overhaul and troubleshooting, because the engine that after-burner failure returns factory's troubleshooting accounts for suitable ratio
Example, wherein afterburner ignition is unsuccessfully one of major failure.Made in detail with certain more typical engine for its fault characteristic
Analysis.Successively in interior outfield the failure of loss of ignition repeatedly occurs for the engine.By counting, less than the 1 year machine outside
More than 10 loss of ignition, if changing the relevant annex in have adjusted dry systems in outfield, such as check valve, catalytic site firearm,
Reinforce Fuel Flow Regulator, accelerate Outflow Valve, point circle valve, nozzle exit area sensor etc., do not excluded, can only returned
Factory.The final engine according to the service technique file of formulation repair and in tandem through experiment by failure reason analysis
After-burner installation after qualified, is excluded failure, the engine is all gone well in outer site fire so far.
The content of the invention
It is an object of the invention to provide a kind of method for removing of fanjet afterburner ignition failure, to solve the above-mentioned back of the body
The problem of being proposed in scape technology.
To achieve the above object, the present invention provides following technical scheme：
A kind of method for removing of fanjet afterburner ignition failure, particular content is as follows：
(1) shadow of the flow to igniting that fuel manifold starts fuel feeding is obtained by the analysis to afterburner system operation principle
Ring；
(2) catalytic site firearm and fuel manifold component are carried out flow and practiced shooting to test, obtain jet in fuel jet area
Influence of the angle to igniting.
It is used as further scheme of the invention：The afterburner system includes Afterburning condition and not Afterburning condition.
Compared with prior art, the beneficial effects of the invention are as follows：
The present invention is tested by the way that catalytic site firearm and fuel manifold component are carried out flow and practiced shooting, and can obtain fuel oil total
Tube assembly flow is excessive, influences the efficiency of seed region, lacks remaining oxygen due to great rich oil in booster zone, make oil-gas ratio
Mismatch and cause afterburner ignition to fail；This method is verified through testing and installing, and ignition failure is excluded.
Embodiment
The technical scheme of this patent is described in more detail with reference to embodiment.
Embodiment 1
A kind of method for removing of fanjet afterburner ignition failure, particular content is as follows：
(1) shadow of the flow to igniting that fuel manifold starts fuel feeding is obtained by the analysis to afterburner system operation principle
Ring；
(2) catalytic site firearm and fuel manifold component are carried out flow and practiced shooting to test, obtain jet in fuel jet area
Influence of the angle to igniting.
The afterburner system includes Afterburning condition and not Afterburning condition.
The operation principle of the afterburner system is as follows：
1. Afterburning condition does not include engine speed and is less than 80%NH not Afterburning condition and rotating speed more than 80%NH not
Afterburning condition.Afterburning condition it is electrodeless adjustable from minimum Afterburning condition to full afterburner.Only when engine speed is big
When 80%NH, it can just go booster.
The engine augmented thrust ratio is than larger, and from 10% to 65%, its function is the necessary thrust of increase, so that aircraft can be fast
Speed is taken off and high-speed flight.The method of increase thrust is that exhaust airstream is reheated, and further speeds up air-flow.The side of reheating
Method is that fuel oil is sprayed into after-burner, fuel oil is burnt again with the remaining oxygen in combustion gas stream, and the result of burning can be big
Amplitude improves the temperature and pressure of combustion gas, so that the fuel gas exhaust speed increase of spout, thrust increase.
The engine use Afterburning condition Rule adjusting be：It is to protect with reinforcing fuel flow regulation afterbunring room temperature
Afterbunring room temperature is held for maximum.Turbine blow down ratio is adjusted with area of injection orifice, is allowed to fall with the turbine of maximum military state
Asia is than equal.
2. when engine selects to reinforce, synchronous valve and reinforcing selector valve are opened, and high pressure fuel leads to air scavenging
Valve upper chamber, moves down valve, and air is blown down in excision, and the left and right room of piston of adjusting again of spout folding and unfolding valve all leads to high pressure fuel, then
Valve is adjusted to move on to rearmost position (the pre- open position of spout) under spring force, the synchronized valve of high pressure fuel to vapor core pump is (high
The vapor core pump that compression ignition oil pump is used) enter throttling arrangement, vapor core pump low pressure is interrupted valve and inlet throttle valve is opened, vapour core
Pump enters working condition.When vapor core pump low pressure interruption valve is opened, the oilhole on piston rod is cut to the control of catalytic ignition fuel oil
Device and pressure ratio adjuster driving cooling oil, are also turned on high pressure fuel, the high pressure fuel to catalytic ignition fuel controller makes it
Work, then three tunnels of high pressure fuel point output：The first via delivers to catalytic site firearm, lights interior, domestic and abroad evaporator tank fuel oil；Second
Road is to room under Outflow Valve servo piston is accelerated, and servo piston is moved up；3rd tunnel, to Afterburner fuel manifold, is total through point circle valve
Pipe fills fuel oil.Hydraulic oil to the big plunger one side of pressure ratio adjuster self-locking device makes P3 P6 pistons release self-locking, controls spout
Area.
Reinforcing connection is operated in completion in 0.05s, and after-burner, which has been lighted a fire, participates in burning.After 3s, catalytic ignition combustion
Oily controller power cut-off, igniting of ceasing fire.
Knowable to fuel system above, first via high pressure fuel is delivered to after reinforcing is controlled after connecting through catalytic ignition fuel oil
Catalytic site firearm, the second road is to accelerating Outflow Valve；A 3rd tunnel extremely point circle valve.And the high pressure that the first via is gone to catalytic site firearm
Fuel oil is divided into two strands of oil circuits again through check valve, flow nipple, spray orifice from one plume to venturi throat diameter about 0.64mm with
Fuel gas mixture makees catalytic ignition, and this strand of high pressure fuel accounts for check valve and flow nipple entirely comes 10% or so of oily total flow；
Secondly stock high pressure fuel enters in fuel manifold, total pipe diameter about 6mm, house steward has 16 nozzle openings, and oil spout bore dia is about
1.1mm, this strand of high pressure fuel, which is accounted for, comes 90% or so of oily total flow, and its main purpose is to fill fuel oil for fuel manifold, as
Start fuel feeding.
This road flow is one of key factor of igniting success or failure as can be seen here, and it directly affects the efficiency of seed region, if
Booster zone lacks remaining oxygen due to great rich oil, oil-gas ratio is mismatched and is caused loss of ignition.
The operation principle of the catalytic site firearm is as follows：
When engine selects afterburner ignition, one high pressure fuel, this strand of fuel oil are provided by catalytic ignition fuel controller
Sprayed by venturi throat spray orifice (diameter about 0.64mm) in catalytic site firearm housing and and from exhaust mixer come
The main combustion gas of high temperature mixed, formed about 500 DEG C or so of temperature fuel-air mixture, at such a temperature with the platinum on catalysing tube
Rhodium " catalyst " plays violent chemical reaction and releases substantial amounts of heat, the surface temperature of catalysis net is steeply risen an air-fuel mixture
Gas is lighted, and the tongues of fire are bored through stable, and the fuel oil that flame ribs light the ejection of evaporator tank oil transportation circle is passed through two, and on Afterburner fuel manifold
The main fuel formation burning things which may cause a fire disaster that Fuel Injector Bar sprays.Make afterburner ignition and normal combustion.When going booster, catalytic ignition fuel oil
Controller works, by check valve, and flow nipple starts fuel feeding, and about 1s is i.e. to catalytic site firearm oil-feeding points fire.Catalytic ignition fires
There is individual timer in oily controller, it is the fuel feeding for being cut to catalytic site firearm that it, which controls valve 3s,.Each afterburner ignition total time
Less than 5s.
It is for analyzing failure cause, the original-pack after-burner AU309 on engine catalytic site firearm and fuel oil is total
Tube assembly carries out flow and practiced shooting to test, and result of the test is shown in Table 1.
The catalytic site firearm fuel oil test data of table 1
As it can be seen from table 1 house steward's flow test is tested in four different required pressures and phase with venturi tube flow
1min is surveyed under same oil temperature condition.The flow measured value of house steward is more much bigger than nominal value respectively, is the 129% of nominal value respectively
~142%, 107%~145%, 107~141%, 106%~142%.The pressure of house steward, venturi pressure and flow are normal.
If flow angle is small, oil is sprayed onto on assembly housing (interconnector), has high-temperature gas mixture to be easy to ablation in pipe；If penetrating
Flow angle is big, it is clear that not in qualified area, penetrates and is helped less than biography flame, also not combustion-supporting, it can be seen that flow angle is also to light a fire into
One of key factor lost.
The present invention is tested by the way that catalytic site firearm and fuel manifold component are carried out flow and practiced shooting, and can obtain fuel oil total
Tube assembly flow is excessive, influences the efficiency of seed region, lacks remaining oxygen due to great rich oil in booster zone, make oil-gas ratio
Mismatch and cause afterburner ignition to fail；This method is verified through testing and installing, and ignition failure is excluded.
The failure that fails to afterburner ignition of this patent has done detailed analysis, to the work of after-burner and catalytic site firearm
Make principle to further investigate with performance, and embodiment is explained in detail.This patent is not limited to above-mentioned embodiment,
In the knowledge that one skilled in the relevant art possesses, it can also be made on the premise of this patent objective is not departed from
Various change.
Claims (2)
1. a kind of method for removing of fanjet afterburner ignition failure, it is characterised in that particular content is as follows：
(1) fuel manifold is obtained by the analysis to afterburner system operation principle and starts influence of the flow of fuel feeding to igniting；
(2) catalytic site firearm and fuel manifold component are carried out flow and practiced shooting to test, obtain flow angle in fuel jet area
Influence to igniting.
2. the method for removing of fanjet afterburner ignition failure according to claim 1, it is characterised in that the reinforcing
System includes Afterburning condition and not Afterburning condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710396115.0A CN106959213A (en) | 2017-05-28 | 2017-05-28 | A kind of method for removing of fanjet afterburner ignition failure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710396115.0A CN106959213A (en) | 2017-05-28 | 2017-05-28 | A kind of method for removing of fanjet afterburner ignition failure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106959213A true CN106959213A (en) | 2017-07-18 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710396115.0A Pending CN106959213A (en) | 2017-05-28 | 2017-05-28 | A kind of method for removing of fanjet afterburner ignition failure |
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| CN (1) | CN106959213A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109596360A (en) * | 2018-11-29 | 2019-04-09 | 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 state efflux door swing troubleshooting methodology |
| CN113669167A (en) * | 2021-09-09 | 2021-11-19 | 南京航空航天大学 | Self-adaptive control method and device for boosting fuel actuating mechanism of turbofan engine |
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| JPH0771234A (en) * | 1993-02-10 | 1995-03-14 | Hitachi Ltd | Engine monitoring system using gas sensor and engine exhaust material reducing system |
| CN1336481A (en) * | 2000-07-31 | 2002-02-20 | 丰田自动车株式会社 | Arrangement for controlling timing of the valve of internal combustion engine |
| CN101144430A (en) * | 2007-10-19 | 2008-03-19 | 北京航空航天大学 | Tower type flame holder for rotor engine |
| CN105300698B (en) * | 2015-11-20 | 2018-01-09 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of fanjet ground experiment starting failure method for removing |
| CN106438158B (en) * | 2016-11-07 | 2019-05-03 | 中国人民解放军空军工程大学 | Aero-engine main chamber based on plasma jet ignition |
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2017
- 2017-05-28 CN CN201710396115.0A patent/CN106959213A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0771234A (en) * | 1993-02-10 | 1995-03-14 | Hitachi Ltd | Engine monitoring system using gas sensor and engine exhaust material reducing system |
| CN1336481A (en) * | 2000-07-31 | 2002-02-20 | 丰田自动车株式会社 | Arrangement for controlling timing of the valve of internal combustion engine |
| CN101144430A (en) * | 2007-10-19 | 2008-03-19 | 北京航空航天大学 | Tower type flame holder for rotor engine |
| CN105300698B (en) * | 2015-11-20 | 2018-01-09 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of fanjet ground experiment starting failure method for removing |
| CN106438158B (en) * | 2016-11-07 | 2019-05-03 | 中国人民解放军空军工程大学 | Aero-engine main chamber based on plasma jet ignition |
Non-Patent Citations (1)
| Title |
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| 郑惠金: "某涡扇发动机加力点火故障分析与排除", 《红旗技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109596360A (en) * | 2018-11-29 | 2019-04-09 | 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 state efflux door swing troubleshooting methodology |
| CN109596360B (en) * | 2018-11-29 | 2020-05-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for eliminating swinging fault of nozzle regulating sheet in stress application state of aircraft engine |
| CN113669167A (en) * | 2021-09-09 | 2021-11-19 | 南京航空航天大学 | Self-adaptive control method and device for boosting fuel actuating mechanism of turbofan engine |
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Application publication date: 20170718 |
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