CN110953082B - Method for eliminating airplane slow-vehicle parking fault with high reliability - Google Patents
Method for eliminating airplane slow-vehicle parking fault with high reliability Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 42
- 239000000446 fuel Substances 0.000 claims abstract description 75
- 238000012216 screening Methods 0.000 claims abstract description 12
- 239000003921 oil Substances 0.000 claims description 150
- 238000012423 maintenance Methods 0.000 claims description 9
- 239000010687 lubricating oil Substances 0.000 claims description 5
- 238000004140 cleaning Methods 0.000 claims description 4
- 230000008030 elimination Effects 0.000 claims description 3
- 238000003379 elimination reaction Methods 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 230000006872 improvement Effects 0.000 claims description 2
- 238000013024 troubleshooting Methods 0.000 abstract 1
- 230000008859 change Effects 0.000 description 14
- 239000000295 fuel oil Substances 0.000 description 14
- 238000012360 testing method Methods 0.000 description 8
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- 238000013016 damping Methods 0.000 description 5
- 230000001105 regulatory effect Effects 0.000 description 5
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- 238000002347 injection Methods 0.000 description 3
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/30—Controlling fuel injection
- F02D41/3082—Control of electrical fuel pumps
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/08—Safety, indicating, or supervising devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D11/00—Arrangements for, or adaptations to, non-automatic engine control initiation means, e.g. operator initiated
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
- F02M37/04—Feeding by means of driven pumps
- F02M37/18—Feeding by means of driven pumps characterised by provision of main and auxiliary pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D2200/00—Input parameters for engine control
- F02D2200/02—Input parameters for engine control the parameters being related to the engine
- F02D2200/10—Parameters related to the engine output, e.g. engine torque or engine speed
- F02D2200/101—Engine speed
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Abstract
The invention introduces a method for eliminating a slow-vehicle parking fault of an airplane with high reliability, solves the slow-vehicle parking fault of the Cirrus SR20 airplane, comprises the steps of screening the performance of a main pump of a TCM IO-360-ES engine, and determining whether to replace the slow-vehicle parking fault according to the stability degree of a slow-vehicle working point; the optimal setting of the optimal reference working point of the engine in the normal slow-speed state is carried out with the aim of reducing the influence degree of the auxiliary pump on the main pump; the comprehensive performance of the fuel system of the aircraft-engine is monitored and checked in operation practice with the aim of real-time control of the performance of the engine. The invention can conveniently monitor the deviation condition of the main pump reference working point and control the performance of the engine in real time; the parameter setting is well documented, the troubleshooting and the piece changing are purposeful, and the reliability of removing the slow-car parking fault of the SR20 airplane is improved.
Description
Technical Field
The invention relates to an aircraft maintenance technology, in particular to a method for eliminating a slow-vehicle parking fault of an aircraft with high reliability, and more particularly relates to a method for eliminating a Cirrus SR20 slow-vehicle parking fault of the aircraft.
Background
The SR20 airplane manufactured by Cirrus Design company in the United states is called as an aerial BMW, adopts a complete machine composite material structure and is provided with a complete machine parachute system, has excellent flight quality and higher safety, is widely applied to the aspects of private use, flight training and the like, and the global holding amount of the SR series airplanes of the Cirrus company exceeds 6000.
The Cirrus SR20 airplane is provided with an IO-360-ES type aviation piston engine produced by American TCM company, and the ground slow-vehicle parking fault of the engine often occurs in the operation, particularly the engine parking occurs in the process that the airplane breaks away from a runway after landing for many times, which brings great psychological pressure to pilots.
There are two fuel supply pumps in the Cirrus SR20 aircraft and engine fuel systems. One is an electric fuel booster pump (hereinafter referred to as an auxiliary pump) located in the aircraft fuel system, which is manually turned on only when needed to assist in fuel supply; the other is an engine-driven fuel pump (hereinafter referred to as primary pump) in an engine fuel system, which is a core component of the engine fuel control system and is the primary pump in the working process of the engine, and the output oil pressure at a specific rotating speed of the primary pump determines the reference working point of the engine. And the auxiliary pump is positioned in front of the main pump on the installation logic, and the fuel output by the auxiliary pump enters the main pump after being filtered by the main fuel. The output pressure of an auxiliary pump is regulated to be between 4 and 6psi in a Cirrus SR20 aircraft maintenance manual, the output oil pressure of a main pump is regulated to be between 7 and 9psi when the reference working point range of the main pump is regulated in a TCM IO-360-ES engine manual at 600rpm in the manual, only the normal regulated range of the output oil pressure of a main oil pump and an auxiliary oil pump is regulated in the manual and related technical documents of factories, and no additional description and requirement are made on the corresponding relation between the output pressures of the main oil pump and the auxiliary oil pump.
There are three manifestations of engine slow stop that are common in operation practice with Cirrus SR20 aircraft: firstly, after the airplane lands on the ground, the accelerator is retracted to a slow state and then the engine is stopped, namely the 'landing stop', the engine stop occurs in the process that the airplane just lands on the ground and is separated from the runway, and the 'landing stop' brings great psychological pressure to the pilot because the airplane is greatly threatened to the single-engine Cirrus SR20 airplane because the airplane just lands and the parking is still close to the ground if the parking fault occurs for several minutes early; secondly, after the auxiliary pump is started on the ground, the rotating speed of the engine is continuously reduced until the engine is stopped, namely the engine is stopped after the auxiliary pump is started; and thirdly, the auxiliary pump is closed to stop the engine at the moment, namely, the pump is closed to stop the engine. Slow car stops are inherent faults in Cirrus SR20 aircraft, and although Cirrus SR series aircraft have kept more than 6000 aircraft worldwide, this problem has not been effectively solved for many years; TCM is a global aviation piston engine manufacturing company, and its products are not exclusively used in Cirrus SR series airplanes, and mostly adopt engine fuel injection systems with similar principles, but TCM company does not disclose the occurrence mechanism of slow stop faults frequently appearing in the operation of its engines. In the field of aviation maintenance engineering, no academic report is made on a method for eliminating a slow-stop fault of an engine related to a TCM fuel injection system. Because the fault reason is unknown, the engine slow-vehicle parking fault frequently occurring in operation practice brings huge psychological pressure to pilots, and for this reason, maintenance technicians can only replace a large number of related parts of a fuel system on the fault engine, so that huge manpower and material resource loss is brought, and a large flight safety risk is brought. And the failure mechanism is unclear, the risk evaluation on the probability of the engine parking in the air is difficult, and based on safety consideration, the operation of the SR20 fleet is suspended until effective measures are taken by the government airworthiness supervision department aiming at the operation condition that the SR20 fleet of a certain aviation operation unit frequently has the engine ground slow vehicle parking.
Through the intensive research and long-time practice verification of the occurrence mechanism of slow vehicle parking trouble faults such as 'landing parking', 'pumping parking' and 'pump shutdown' of the Cirrus SR20 airplane in the operation practice, the invention provides a judgment standard and an execution method convenient for engineering practice operation for reliably solving the slow vehicle parking trouble of the Cirus SR20 airplane, and the technical scheme disclosed by the invention has greater reference significance for solving similar troubles on other models adopting a TCM engine fuel injection control system because the screening judgment on the performance of a TCM IO-360-ES engine main pump is involved.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for eliminating the parking fault of the slow airplane with high reliability, in particular to a method for eliminating the parking fault of the slow airplane of the Cirrus SR20, which reliably solves the problem that the intractable slow-car parking fault such as 'landing parking', 'pumping stopping' and the like frequently occurs in the normal operation of the Cirrus SR20 airplane; the invention further solves the technical problems that the invention also comprises an operation method and parameter standards for conveniently monitoring and judging the comprehensive performance of an airplane-engine fuel system on a Cirrus SR20 airplane with the aim of preventing various slow car parking faults of the TCMIO-360-ES engine, thereby achieving the purposes of tracking and monitoring the performance condition of the engine in real time, finding the fault trend as soon as possible and solving the intractable slow car parking fault of the Cirrus SR20 airplane with higher reliability; the technical problem to be further solved by the invention also comprises that the economical efficiency is considered on the basis of meeting the requirement of the prior art, and the performance of the high-price components which cannot pass the performance detection and are to be eliminated, such as an engine-driven fuel pump, is optimized, so that the use value of the components is recovered.
In order to solve the technical problems, the invention adopts the following technical scheme:
a method for eliminating a slow-vehicle parking fault of an airplane with high reliability is particularly used for solving the slow-vehicle parking fault of the Cirrus SR20 airplane, and comprises the following steps:
the first stage is as follows: with the purpose of high-quality elimination, the performance screening of a main pump (an engine-driven fuel pump) of a TCM IO-360-ES engine is carried out, and whether the main pump is replaced is determined by measuring the stability degree of a slow work point of the main pump;
the method comprises the following steps of performing secondary screening on a main pump qualified by factory test in an aircraft running link by using the stability of a slow vehicle (working point) as an index, and mainly measuring the stability degree of the slow vehicle working point of the main pump by simulating various use states of an engine in actual operation of the aircraft in engine ground test and using the drift amount of a reference working point as a quantitative index;
in actual operation, an auxiliary pump needs to be started during takeoff and landing stages of the airplane, and an additional force for pushing the opening of the slow car valve to be increased exists in a fuel oil film of a return oil chamber of the main pump in the starting state of the auxiliary pump, so that the opening of the slow car valve is further increased due to the starting of the auxiliary pump during the takeoff of the full throttle of the airplane; the test of the slow vehicle stability of the main pump is to simulate the actual running state of the airplane to maximize the opening degree of the slow vehicle valve, and then the accelerator is withdrawn to investigate the capacity of resetting the slow vehicle valve to the reference opening degree;
the method comprises the following specific steps:
1) starting the engine at the lowest possible starting speed, and if the temperature of the engine and the temperature of lubricating oil are lower than the temperature specified values of the technical manual of the engine, finishing the warming-up operation according to a specified program;
2) stabilizing the rotating speed of the engine at a calibrated rotating speed of 600rpm, and recording the output oil pressure of a main pump of the engine, wherein the oil pressure is called as non-metering fuel pressure in a Cirrus SR20 technical handbook, and is set as P1; adjusting the main pump slow vehicle oil pressure adjusting screw to make P1 between 7-9psi when necessary;
3) pushing the accelerator to the maximum power position, starting an auxiliary pump, namely the electric fuel booster pump, retracting the accelerator after working for 3-5s in the full accelerator state, and closing the auxiliary pump when the engine rotates at about 1500-2000 rpm;
4) continuing to receive the accelerator to the engine calibration rotating speed of 600rpm, and recording the output oil pressure of the main pump of the engine, wherein the output oil pressure is P2;
5) calculating the difference between P1 and P2, setting delta P = P1-P2, wherein the larger the difference is, the worse the stability of the main pump is, if the delta P is more than or equal to 2psi, the main pump can be judged to have the performance which can not meet the normal operation requirement, and the main pump is replaced;
and a second stage: aiming at reducing the influence degree of the auxiliary pump on the main pump, the optimal setting of the optimal reference working point of the engine in the normal slow-moving state of the Cirrus SR20 airplane is carried out:
according to the specification of a TCM IO-360-ES type engine technical manual, a reference working point is set on a calibration rotating speed of 600rpm, but a slow turning rotating speed normally used in the operation of an airplane is 800 +/-50 rpm, so that the airplane can be put into operation after the engine slow turning rotating speed is adjusted to 800 +/-50 rpm after the reference working point is set at 600 rpm; engineering practice shows that the mixing ratio parameter set at 600rpm is not suitable for 800 +/-50 rpm, and needs to be adjusted again at the rotating speed of 800 +/-50 rpm, which can affect other parameters set on the reference working point, and the operation is repeated, so that the operation is time-consuming and labor-consuming;
the optimization steps are as follows:
1) starting the engine, and if the temperature of the engine and the temperature of the lubricating oil are lower than the temperature specified values of the technical manual of the engine, finishing the warming-up operation according to a specified program until the temperature meets the specified value range;
2) pushing the accelerator to the engine speed of 1700 +/-100 rpm and continuously cleaning the spark plug for 10-15 s;
3) the Cirrus SR20 airplane which receives the accelerator to 800 +/-50 rpm normally runs at the slow speed to check whether the airplane is lean or rich, and the variation of the engine speed is about 70 +/-10 rpm; adjusting a slow vehicle lean and rich oil adjusting screw when necessary;
4) adjusting the rear-pushing accelerator to 1700 +/-100 rpm for 10-15s to clean the spark plug;
5) the accelerator is retracted to 800 +/-50 rpm again, the actual rotating speed of the engine at the moment is recorded as N1, and N1 is the actual rotating speed of the slow vehicle when the auxiliary pump is not started; after an auxiliary pump, namely an electric fuel booster pump, is started, the actual rotating speed of the engine is recorded to be N2, and N2 is the actual rotating speed of the engine after the auxiliary pump is started; changing quantity of engine speed, delta N = N2-N1, and meeting the requirement that | delta N | ≦ 50 rpm;
because the auxiliary pump is started in an engine fuel system of the airplane to influence the fuel supply pressure of the main pump, the fuel-air ratio of the engine can be changed and reflected by the change of the rotating speed of the engine. Checking the oil-gas ratio at 800RPM for the first time, namely determining whether the oil-gas ratio of the engine in the rotating speed state is proper or not, cleaning a spark plug, and returning to 800RPM again, wherein the oil-gas ratio basically does not change; and then starting the auxiliary pump, wherein the oil-gas ratio can be greatly changed under the influence of the auxiliary pump, the stability and the reliability of the engine are measured through the engine rotating speed change value, and the larger the rotating speed change value is, the larger the oil-gas ratio change value is. Therefore, the influence degree of the auxiliary pump on the main pump is actually measured through the variable of the engine speed;
6) if delta N < -50rpm, increasing the output oil pressure of a main pump, namely an engine-driven fuel pump, wherein the output oil pressure is non-metering fuel pressure; if the delta N is more than 50rpm, reducing the output oil pressure of the main pump; repeating the second stage step 2) to the second stage step 5) after each adjustment;
7) when the accelerator is withdrawn to 600rpm of the engine calibration speed, checking that the output oil pressure of a main pump (an engine drives a fuel pump) is in a range of 7-9psi, and if the output oil pressure exceeds the range and cannot meet the step 6 of the second stage, replacing an auxiliary pump (an electric fuel booster pump);
8) when the auxiliary pump is replaced, a proper auxiliary pump is selected according to the output oil pressure of the main pump in the second stage step 7), if the output oil pressure of the main pump is greater than 9psi, the auxiliary pump with the lower limit of the output oil pressure is selected, and otherwise, the auxiliary pump with the upper limit of the output oil pressure is selected if the output oil pressure is less than 7 psi; after the auxiliary pump is replaced, the steps 1) to 7) of the second stage are repeatedly executed for readjustment;
and a third stage: the method aims at controlling the performance of the engine in real time, and monitors and checks the comprehensive performance of the fuel system of the aircraft-engine in operation practice:
the technical manual of the TCM IO-360-ES type engine adopts oil pressure to judge the reference working point of a main pump, the rotating speed of the engine needs to be reset to a specified calibration rotating speed when the judgment is executed, and special test equipment needs to be accessed, so that the operation is complicated, the test and the monitoring can not be carried out at any time during the operation of an airplane, and the real-time control on the performance condition of the engine is inconvenient;
considering that engine fuel is incompressible low-viscosity fluid, an engine fuel system also accords with the general principle of a hydraulic system, and the fact that the fuel pressure and the fuel flow have a certain corresponding relation under the condition that the inner channel aperture of a pipeline of the fuel system is certain can be known; meanwhile, the principle of the aero-engine shows that when the opening degree of an accelerator is unchanged, the change of the fuel oil flow of the engine can cause the change of the oil-gas ratio of the gas mixture in the cylinder, and the change is finally reflected on the change of the rotating speed of the engine. Based on the above and considering the requirement of convenience of operation in the actual operation environment, the invention provides the method for quantitatively judging the deviation degree of the reference working point of the main pump by taking the rotating speed of the engine and the fuel flow of the engine as reference quantities;
the method comprises the following implementation steps:
1) when the accelerator is closed to reach the normal slow-speed rotating speed of 800 +/-50 RPM, recording the actual rotating speed of the engine at the moment as N3, wherein N3 is the actual slow-speed rotating speed when the auxiliary pump is not started; after an auxiliary pump, namely an electric fuel booster pump, is started, the actual rotating speed of the engine is recorded to be N4, and N4 is the actual rotating speed of the engine after the auxiliary pump is started; changing the engine speed by delta N2= N4-N3, and meeting the requirement that |. DELTA N2 | ≦ 50rpm, otherwise, returning to the first stage and the second stage;
2) check the minimum fuel flow at a specific speed of the engine: 800rpm should not be less than 1.3gph, 900rpm should not be less than 1.4gph, otherwise return to the first stage and the second stage;
3) during maintenance, the second stage is performed, for example, by replacing the auxiliary pump.
On a Cirrus SR20 airplane-loaded TCM IO-360-ES aviation piston engine, an engine-driven fuel pump (hereinafter referred to as a main pump) is a core component of an engine fuel control system and provides proper fuel pressure for the engine in different rotating speed states. The main pump consists of a pressurizing unit and a control unit, wherein the pressurizing unit is a rotary plate pump, and the control unit consists of a cart valve, a slow car valve and a mixing ratio valve. Because the rotary plate pump is a constant volume pump, the fuel oil discharged every time the rotary plate pump rotates for one circle is fixed, in order to ensure sufficient fuel oil supply, the fuel oil output by the rotary plate pump is larger than the actual requirement of the engine at any rotating speed of the engine, and redundant fuel oil returns to the inlet of the rotary plate pump through an oil return channel provided by the control unit. Due to the incompressibility of the oil, the control unit actually ensures that the main pump outputs proper fuel pressure by performing proper oil return on the output end of the pressurizing unit. The control unit provides two parallel oil return channels for the output end (output oil chamber) of the rotary plate pump, one of the two oil return channels is formed by a large vehicle valve and a slow vehicle valve which are connected in series, fuel oil enters the middle oil chamber through the large vehicle valve and then flows to the oil return oil chamber through the slow vehicle valve, and the oil return amount of the channel can be automatically controlled according to preset conditions and external environmental conditions; the other oil return channel is independently composed of a mixing ratio valve, the mixing ratio valve is in a closed state (full rich oil level) in a normal state, and the oil return amount is controlled by manually operating the opening degree of the valve when needed. When the mixing ratio is full rich, the excess fuel output by the rotary plate pump and exceeding the actual requirement of the engine flows to the oil return chamber through the passage of the 'cart valve-slow cart valve'.
The slow-moving valve is a disc-shaped valve which is sleeved on the core column and can axially move along the core column, and the core column is a section of cylindrical straight guide rod fixed on the base. The sectional areas of two ends of the valve body are different, the center position of the large end is provided with a blind hole along the axial direction, and the blind hole is sleeved on the core column and matched with the core column to jointly provide circumferential positioning for the valve so as to ensure the stability of the valve body in the axial moving process on the core column. The middle oil chamber is arranged in front of the slow-speed valve, the oil return chamber is arranged behind the slow-speed valve, and the fuel oil pressure difference between the middle oil chamber and the oil return chamber provides large opening force for the slow-speed valve; the slow motion valve body is axially moved on the core column according to different oil pressures of the middle oil chamber on the basis of a certain spring pretightening force to change a gap between the valve body and the base, namely to change the opening degree of the valve. The fuel film provides sealing and isolation between the oil return oil chamber and the diaphragm capsule chamber where the slow-speed vehicle oil pressure spring is located, the axial position of the screw is changed when the slow-speed vehicle oil pressure adjusting screw is adjusted, the base pre-tightening force of the slow-speed vehicle oil pressure spring on the slow-speed vehicle valve body is changed, and the base oil return quantity of the middle oil chamber through the slow-speed vehicle valve is also controlled.
The output oil pressure of the main pump at a specific calibrated rotating speed determines the reference working point of the engine. The reference operating point was adjusted at 600 as specified in the TCM IO-360-ES engine technical ManualrpmWhen the engine rotates, the slow vehicle oil pressure adjusting screw on the main pump is adjusted to ensure that the output oil pressure of the main pump is between 7 and 9psiIn the meantime. After the reference working point of the engine is set, the slow moving valve is balanced under the combined action of certain fuel oil pressure of the intermediate fuel chamber and a slow moving fuel oil pressure spring, the slow moving valve keeps certain opening degree, the reference opening degree is set, and correspondingly, the position of the slow moving valve body on the core column at the moment is also called as a reference position. After the rotating speed of the engine is changed, the fuel oil quantity output by the supercharging unit is changed, the oil pressure of a middle oil chamber in front of the slow valve is changed due to incompressibility of oil, the balance of the slow valve body is broken, the slow valve body moves the core column and reaches balance at a new position, at the moment, the opening of the slow valve is changed, and the oil return quantity is changed. The opening degree of the slow car valve reaches the maximum under the full-throttle state. According to the description of TCM IO-360-ES type engine technical manual, parameters such as mixing ratio and the like set in a reference state will affect the overall performance of the engine at each rotating speed, the reference working point of the engine is not doubt stable, namely, the throttle is closed to a calibration position again after the engine works in a full throttle state, and a slow vehicle valve body can return to the reference positionLocation. However, engineering practice shows that on the engines of some Cirrus SR20 airplanes, after passing through a full throttle and returning to a slow car state again, the originally set slow car mixing ratio and other parameters are found to be changed greatly, and 600 shows thatrpmThe output oil pressure of the main pump is lower than the previous set value after retesting on the calibrated rotating speed, which indicates that the slow car valve body does not return to the reference position, and the opening degree of the slow car valve is larger than the reference opening degree, so that the oil return quantity of an oil return channel of the big car valve-slow car valve is increased, the output oil pressure of the main pump is reduced, namely the reference working point of the engine is deviated.
Each engine has its own individual characteristics influenced by various factors such as assembly process, the manual only gives the normal allowable range of the primary pump reference working point, the specific factors should be referred to on the specific engine to finally decide the specific value of the reference working point, but no description is provided, the related technical documents do not disclose, in the engineering practice, the worker mainly relies on personal experience to set the primary pump reference working point, so that the final reference working point is 7-9psiHas a certain randomness in the normal range, or uniformly sets the reference working points of all the engines at the middle value 8 of the normal range in a cutting way so as to ensure that the data are not easily out of limitpsiIn the above, these operations obviously kill the individual characteristic differences of the engines, and most of the engines are deviated from the optimal reference working point with high probability.
In the main pump, the oil return chamber is communicated with the fuel inlet of the main pump, namely the control unit returns the redundant fuel to the fuel inlet of the main pump for recycling, so that the oil pressure in the oil return chamber is equal to the oil pressure of the fuel inlet of the main pump. The setting of the reference working point of the main pump is carried out under the state that the auxiliary pump is not started, and the oil pressure of the oil return chamber and the oil pressure of the inlet of the main pump are both 0psi. In the state of opening the auxiliary pump, a certain oil pressure exists in the inlet of the main pump and the oil return chamber of the main pump, the oil pressure is equal to the output oil pressure of the auxiliary pump, the oil pressure exists in the oil return chamber in the main pump, and on one hand, the oil pressure acts on a fuel oil film to push the opening of the slow car valve to be increasedThe additional force increases the oil return amount, and on the other hand, the oil return amount is reduced due to the back pressure of the fuel oil in the middle oil chamber returning through the slow car valve, so that the output oil pressure of the auxiliary pump can bring certain influence on the main pump, but how the final output oil pressure of the main pump changes cannot be summarized according to different specific conditions. If the output oil pressure of the auxiliary pump is 4-6psiThe upper region of the normal range and the reference working point of the main pump are set at 7-9psiWhen the engine is in a lower area in a normal range, the back pressure after the auxiliary oil supply pump is started can become a main factor to reduce the final oil return amount, the oil output pressure of the main pump deviates towards the rising direction of the oil pressure, so that the oil-gas mixture is reduced in the rotating speed of the rich-side engine due to the fact that more oil is supplied to the engine, and the engine is stopped in a mode of being rich in oil when exceeding a certain threshold value, which is called as pump-pumping stopping in practice; on the contrary, the additional force can be a main factor to increase the final oil return amount, the output oil pressure of the main pump deviates towards the oil pressure reduction direction, the oil is less supplied to the engine to increase the rotating speed of the oil-gas mixture lean towards the engine, the engine is stopped in the case of over lean oil when exceeding a certain threshold value, and the engine is stopped in the practice of pumping. So "pump-off" occurs during the period that the auxiliary pump is continuously on. If the influence degree of the auxiliary pump on the main pump is within a certain threshold, the engine does not stop during the starting of the auxiliary oil supply pump, but in a short time that the back pressure and the additional force disappear at the same time and the slow valve does not return to the original position at the moment of closing the auxiliary oil supply pump, the oil return amount is excessive due to the large opening factor of the slow valve, so that the output oil pressure of the main pump is too low, and the engine stops in an oil-poor state, which is practically called as 'pump-off stopping'. So "pump shutdown" occurs at the instant the auxiliary pump is turned off.
Engineering practice shows that the deviation of the reference working point of the main pump always faces the direction of fuel pressure reduction, which causes the lean oil of the engine in a slow running state, and the lean oil stop is induced when a certain threshold value is exceeded. The deviation is absolute, the deviation is relative, the main pump with the overlarge deviation amount is judged to be unqualified and is replaced, the screening standard is a secondary test carried out on the main pump qualified by a factory test in the aircraft operation link, and the screening standard is higher than the factory standard. The targeted operation judgment method and the screening standard are not disclosed in the factory and the relevant technical field literature, and are one of the innovative points of the invention.
Based on the design principle of the main pump, the main pump subjected to secondary screening is still influenced by the output oil pressure of the auxiliary pump, so that the influence of the auxiliary pump on the main pump is one of the non-negligible slow vehicle parking inducements.
The performance change caused by the combination of various influence factors such as abrasion, environmental condition change and the like exists in any mechanical part in use, how to effectively monitor the performance drift of the main pump under the aircraft running condition and how to carry out quantitative judgment is not disclosed in related technical documents, and an operation method and parameter standards which aim to prevent various slow vehicle parking faults of the TCM IO-360-ES engine and are convenient for monitoring and judging the combination performance of the aircraft-engine fuel system of the Cirrus SR20 aircraft in engineering practice are provided, so that the invention is the third innovation point.
Particularly, it is clear from the technical manual of the TCM IO-360-ES type engine that the primary pump reference operating point needs to be set again after the components of the engine fuel system are replaced, and the auxiliary pump belongs to the engine body fuel system, so that the primary pump reference operating point is not set after the auxiliary pump is replaced in the engineering practice. Because the output oil pressures of different auxiliary pumps have individual differences, the verification of the reference working point of the main pump and the resetting when necessary are required after the auxiliary pump is replaced on the basis of the second innovation point, and the fourth innovation point is the invention.
After the technical scheme of the innovation points is effectively implemented, various engine slow-vehicle parking faults of the Cirrus SR20 airplane can be effectively prevented and reliably solved. In the technical scheme, the primary pump which cannot pass through secondary screening is eliminated, and the pump is a core component of the fuel system of the engine and is expensive, so that certain economic loss exists in direct elimination; in order to improve the economy, the invention also provides a slow vehicle valve body oil way improvement method based on the optimization of the stability performance of the slow vehicle valve of the main pump, which is the fifth innovation point of the invention.
By adopting the technical scheme, the invention has the following beneficial effects:
1) the system can conveniently monitor the deviation condition of the reference working point of the main pump, and can realize real-time control on the performance of the engine.
Because the Cirrus SR20 airplane is not provided with an onboard fuel pressure gauge and can not display the fuel pressure parameter output by the main pump in real time, the technical scheme disclosed by the invention adopts the existing engine rotating speed and engine fuel flow parameter on the airplane to judge and monitor the key indexes such as the deviation degree of the main pump reference working point and the like, the rotating speed of the engine and the access of special equipment are not required to be reset as the traditional method is, the correctness judgment of the main pump reference working point can be finished in normal operation, the operation method is simple and easy to implement, the key parameters of the engine can be conveniently monitored in the airplane operation, the performance condition of the engine can be controlled in real time in the airplane operation, and the safety requirement can be met.
2) The parameter setting is well-documented, the fault clearing and part changing are purposeful, the process is simple, the effect is good, the waste of manpower and material resources is reduced, and the economic index is good.
Before the method is published by the invention, performance characteristics, test judgment methods and parameter standards of a Cirrus SR20 aircraft primary pump (an engine-driven fuel pump) are not disclosed by aircraft and engine manufacturers, and no related academic research report exists in the field of aviation maintenance engineering. According to the traditional method recommended by manufacturers, when the reference working point of the engine is set, the output fuel pressure of the fuel pump driven by the engine is adjusted within the range of 7-9psi only under the specified 600rpm calibration rotating speed state, the specific setting value is completely dependent on the subjective will and maintenance experience of an operator, so that the final reference working point has certain randomness within the normal range of 7-9psi, or the reference working points of all the engines are uniformly set on the middle value of 8psi of the normal range of 7-9psi in a cutting mode so as to prevent data from exceeding the limit. The operating method does not take account of individual characteristic difference factors of the engine, so that the deviation of the reference working point of the main pump from the optimal position is likely to occur, the influence of an auxiliary pump (an electric fuel booster pump) on the main pump is not considered, but the technical file system has no reference criterion and has no research report in the academic field, so that the slow vehicle parking fault mechanism of the engine of the Cirrus SR20 airplane is unclear for a long time, and a large amount of manpower and material resources are difficult to effectively solve.
During the verification period in engineering practice, through the execution of a series of technical schemes such as secondary screening of the performance of the main pump and the like, the parameter setting is well documented, fault removal and part replacement are purposeful, the process is simple and good in effect, the waste of manpower and material resources is reduced, and the economic index is better.
Drawings
FIG. 1 is a schematic diagram of an oil return channel of a large valve and a slow valve pair output oil chamber of a TCM IO-360-ES aviation piston engine mounted on a Cirrus SR20 airplane.
FIG. 2 is an enlarged view of a slow valve oil circuit of a large valve and a slow valve pair output oil chamber of the TCM IO-360-ES aviation piston engine.
In the figure, 1-a large vehicle valve, 2-an output oil chamber, 3-an intermediate oil chamber, 4-a slow vehicle valve, 5-an oil return oil chamber, 6-a core column, 7-a fuel oil film, 8-a film box cavity communicated with an atmospheric hole, 9-a slow vehicle oil pressure adjusting screw, 10-a slow vehicle oil pressure spring, 11-a slow vehicle valve seat and 12-a damping cavity.
Detailed Description
The patent is further explained below with reference to the figures and examples. The scope of protection of the patent is not limited to the specific embodiments.
Example 1
As shown in FIGS. 1-2, the patent discloses a method for reliably eliminating a slow-vehicle parking fault of an airplane, and particularly aims to solve the problem of the slow-vehicle parking fault of the Cirrus SR20 airplane.
The first stage is as follows: the method comprises the steps of screening the performance of a main pump of the TCM IO-360-ES engine by aiming at the excellence and the disadvantage, and determining whether to replace the main pump or not by measuring the stability degree of a slow work point of the main pump. The primary pump, i.e., the engine, drives the fuel pump.
The method comprises the following specific steps:
1) starting the engine at a starting speed as low as possible, and if the engine temperature and the oil temperature are lower than specified values, completing the warming-up operation according to a specified program;
2) stabilizing the rotating speed of the engine at a calibrated rotating speed of 600rpm, and recording the output oil pressure P1 of a main pump of the engine;
3) pushing the accelerator to the maximum power position and starting the auxiliary pump, retracting the accelerator after working for about 3-5 seconds in the full accelerator state, and closing the auxiliary pump when the engine rotates at about 1500-;
4) continuously retracting the accelerator to the engine calibration rotating speed of 600rpm, and recording the output oil pressure P2 of the main pump of the engine;
5) and calculating the difference value delta P = P1-P2 between P1 and P2, if the delta P is larger than or equal to 2psi, judging that the performance of the main pump cannot meet the normal operation requirement, and replacing the main pump.
And a second stage: the method aims to reduce the influence degree of the auxiliary pump on the main pump, and the optimal reference working point of the engine of the Cirrus SR20 aircraft in the normal slow-moving state is quickly set.
The method comprises the following implementation steps:
1) starting the engine, and finishing the warming-up operation according to a specified program if the temperature of the engine and the temperature of the lubricating oil are lower than specified values;
2) pushing the accelerator to the engine speed of 1700 +/-100 rpm for 10s to clean the spark plug;
3) the Cirrus SR20 airplane which receives the accelerator to 800 +/-50 rpm normally runs at the slow speed to check whether the airplane is lean or rich, and the variation of the engine speed is about 70 +/-10 rpm; adjusting a slow vehicle lean and rich oil adjusting screw when necessary;
4) adjusting the rear-pushing accelerator to 1700 +/-100 rpm for 15s to clean the spark plug;
5) the accelerator is withdrawn again to 800 +/-50 rpm, and the actual rotating speed of the engine at the moment is recorded as N1 (the actual slow vehicle rotating speed when the auxiliary pump is not started); after an auxiliary pump, namely an electric fuel booster pump, is started, the actual rotating speed of the engine is recorded as N2 (the actual rotating speed of the engine after the auxiliary pump is started); the engine speed change quantity delta N = N2-N1 should satisfy | Δ N ≦ 50 rpm;
6) if delta N < -50rpm, increasing the output oil pressure of the main pump, namely an engine-driven fuel pump, to obtain non-metering fuel pressure; if the delta N is more than 50rpm, reducing the output oil pressure of the main pump; repeating the second stage from step 2) to step 5) after each adjustment;
7) when the accelerator is withdrawn to the engine calibration rotating speed of 600rpm, checking that the output oil pressure of the main pump is in the range of 7-9psi, and if the output oil pressure exceeds the range, the step 6 cannot be met, replacing the auxiliary pump (the electric fuel booster pump);
8) when the auxiliary pump is replaced, a proper auxiliary pump is selected according to the output oil pressure of the main pump in the second stage step 7), if the output oil pressure of the main pump is greater than 9psi, the auxiliary pump with the lower limit of the output oil pressure is selected when the auxiliary pump is replaced, otherwise, the auxiliary pump with the upper limit of the output oil pressure is selected when the output oil pressure is less than 7 psi; after the auxiliary pump is replaced, the second stage steps 1) to 7) are repeatedly executed for adjustment again.
And a third stage: the comprehensive performance of the fuel system of the aircraft-engine is monitored and checked in operation practice with the aim of real-time control of the performance of the engine.
The method comprises the following implementation steps:
1) when the accelerator is closed to reach the normal slow-speed rotating speed of 800 +/-50 RPM, recording the actual rotating speed of the engine at the moment as N3, wherein N3 is the actual slow-speed rotating speed when the auxiliary pump is not started; after an auxiliary pump, namely an electric fuel booster pump, is started, the actual rotating speed of the engine is recorded to be N4, and N4 is the actual rotating speed of the engine after the auxiliary pump is started; changing the engine speed by delta N2= N4-N3, and meeting the requirement that |. DELTA N2 | ≦ 50rpm, otherwise, returning to the first stage and the second stage;
2) check the minimum fuel flow at a specific engine speed: should not be less than 1.3gph at 800rpm, should not be less than 1.4gph at 900rpm, otherwise return to the first stage and the second stage;
3) if the auxiliary pump is replaced during maintenance, the second stage is required to be executed.
A fourth stage: the slow-speed valve body oil circuit based on the main pump slow-speed valve stability performance optimization is improved:
the bottom of the damping cavity is provided with an unloading hole which penetrates through the oil return oil chamber and the damping cavity, when the core column moves towards the bottom of the central hole of the slow-speed vehicle valve body, oil in the damping cavity is discharged to the oil return oil chamber through the unloading hole, and when the core column moves away from the bottom of the central hole of the slow-speed vehicle valve body, the oil in the oil return oil chamber is guided into the damping cavity through the unloading hole.
After the unloading hole is arranged, the radial fit clearance between the slow-moving valve body and the core column is reduced so as to improve the radial stability of the valve body.
And (3) data statistics:
before the technical scheme is not adopted, 40 Cirrus SR20 airplanes of a certain aviation operation unit are operated for 140870 hours in a cumulative mode within 50 months, the slow vehicle stop fault occurs 75 hours, the average fault rate is 1878 hours/hour, and 1.5/month. On average, slow vehicle parking failures occur every time, which causes economic loss of 1.2 ten thousand yuan.
After the technical scheme is adopted, the 40 Cirrus SR20 airplanes of the aviation operation unit operate for 25474 hours in 5.5 months in an accumulated mode, the slow vehicle parking fault is 3 hours, the average fault rate is 4631 hours/hour, and the average fault rate is 0.5 hour/month.
After the technical scheme is completely adopted, 40 Cirrus SR20 airplanes of the aviation operation unit continuously operate for more than 30 months in the continuous statistical period, the accumulated operation time exceeds 106430 hours, and a slow vehicle parking fault is 0.
Practice evidence shows that the method can effectively eliminate intractable slow-vehicle parking faults of the Cirrus SR20 aircraft which have not been solved by the industry for many years, and has obvious effect on guaranteeing flight safety and obvious social benefit. The economic benefit aspect can save 22 ten thousand yuan for the aviation operation unit every year.
Claims (1)
1. A method for eliminating a slow-vehicle parking fault of an airplane with high reliability is particularly used for solving the slow-vehicle parking fault of the Cirrus SR20 airplane, and is characterized by comprising the following steps:
the first stage is as follows: aiming at the purpose of high-quality elimination, carrying out TCM IO-360-ES engine main pump performance screening, and determining whether to replace the main pump by measuring the stability degree of a slow work point of the main pump;
the method comprises the following specific steps:
1) starting the engine at the lowest possible starting speed, and if the temperature of the engine and the temperature of lubricating oil are lower than the temperature specified values of the technical manual of the engine, finishing the warming-up operation according to a specified program;
2) stabilizing the rotating speed of the engine at a calibrated rotating speed of 600rpm, and recording the output oil pressure of a main pump of the engine, wherein the oil pressure is called as non-metering fuel pressure in a Cirrus SR20 technical handbook, and is set as P1; adjusting the main pump slow vehicle oil pressure adjusting screw to enable the P1 to be between 7 and 9 psi;
3) pushing the accelerator to the maximum power position, starting an auxiliary pump, namely the electric fuel booster pump, retracting the accelerator after working for 3-5s in the full accelerator state, and closing the auxiliary pump when the engine speed is 1500-2000 rpm;
4) continuing to receive the accelerator to the engine calibration rotating speed of 600rpm, and recording the output oil pressure of the main pump of the engine, wherein the output oil pressure is P2;
5) calculating the difference between P1 and P2, setting delta P = P1-P2, wherein the larger the difference is, the worse the stability of the main pump is, if the delta P is more than or equal to 2psi, the main pump can be judged to have the performance which can not meet the normal operation requirement, and the main pump is replaced;
and a second stage: aiming at reducing the influence degree of the auxiliary pump on the main pump, the optimal setting of the optimal reference working point of the engine in the normal slow-moving state of the Cirrus SR20 airplane is carried out:
the improvement steps are as follows:
1) starting the engine, and finishing the warm-up operation according to a specified program if the temperature of the engine and the temperature of the lubricating oil are lower than the specified values of the temperature of the engine technical manual;
2) pushing the accelerator to the engine speed of 1700 +/-100 rpm and continuously cleaning the spark plug for 10-15 s;
3) the Cirrus SR20 airplane which receives the accelerator to 800 +/-50 rpm normally runs at the slow speed to check whether the airplane is lean or rich, and the variation of the engine speed is about 70 +/-10 rpm; adjusting a slow-vehicle lean and rich oil adjusting screw;
4) adjusting the rear-pushing accelerator to 1700 +/-100 rpm and continuously cleaning the spark plug for 10-15 s;
5) the accelerator is retracted to 800 +/-50 rpm again, the actual rotating speed of the engine at the moment is recorded as N1, and N1 is the actual rotating speed of the slow vehicle when the auxiliary pump is not started; after an auxiliary pump, namely an electric fuel booster pump, is started, the actual rotating speed of the engine is recorded to be N2, and N2 is the actual rotating speed of the engine after the auxiliary pump is started; changing quantity of engine speed, delta N = N2-N1, and meeting the requirement that | delta N | ≦ 50 rpm;
6) if delta N < -50rpm, increasing the output oil pressure of a main pump, namely an engine-driven fuel pump, wherein the output oil pressure is non-metering fuel pressure; if the delta N is more than 50rpm, reducing the output oil pressure of the main pump; repeating the second stage step 2) to the second stage step 5) after each adjustment;
7) when the accelerator is withdrawn to 600rpm of the engine calibration speed, checking that the output oil pressure of the main pump is in a range of 7-9psi, and if the output oil pressure exceeds the range, the second stage step 6) cannot be met, replacing the auxiliary pump;
8) when the auxiliary pump is replaced, a proper auxiliary pump is selected according to the output oil pressure of the main pump in the second stage step 7), if the output oil pressure of the main pump is greater than 9psi, the auxiliary pump with the lower limit of the output oil pressure is selected, and otherwise, the auxiliary pump with the upper limit of the output oil pressure is selected if the output oil pressure is less than 7 psi; after the auxiliary pump is replaced, the steps 1) to 7) of the second stage are repeatedly executed for readjustment;
and a third stage: the method aims at controlling the performance of the engine in real time, and monitors and checks the comprehensive performance of the fuel system of the aircraft-engine in operation practice:
the method comprises the following steps:
1) when the accelerator is closed to reach the normal slow-speed rotating speed of 800 +/-50 RPM, recording the actual rotating speed of the engine at the moment as N3, wherein N3 is the actual slow-speed rotating speed when the auxiliary pump is not started; after an auxiliary pump, namely an electric fuel booster pump, is started, the actual rotating speed of the engine is recorded to be N4, and N4 is the actual rotating speed of the engine after the auxiliary pump is started; changing the engine speed by delta N2= N4-N3, and meeting the requirement that |. DELTA N2 | ≦ 50rpm, otherwise, returning to the first stage and the second stage;
2) check the minimum fuel flow at a specific speed of the engine: 800rpm should not be less than 1.3gph, 900rpm should not be less than 1.4gph, otherwise return to the first stage and the second stage;
3) during maintenance, the second stage is performed, for example, by replacing the auxiliary pump.
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| JP2011196262A (en) * | 2010-03-19 | 2011-10-06 | Denso Corp | Fuel pressure control device |
| CN105422296A (en) * | 2015-12-24 | 2016-03-23 | 苏州达菲特过滤技术股份有限公司 | High-pressure common-rail fuel injection pressure control method and system |
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