CN114116833A - Statistical method for accumulated working time of each stage of turboprop engine - Google Patents

Statistical method for accumulated working time of each stage of turboprop engine Download PDF

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CN114116833A
CN114116833A CN202111318517.1A CN202111318517A CN114116833A CN 114116833 A CN114116833 A CN 114116833A CN 202111318517 A CN202111318517 A CN 202111318517A CN 114116833 A CN114116833 A CN 114116833A
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山磊
马静坡
高峰
艾波
黄超
邓锐
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Shaanxi Qianshan Avionics Co Ltd
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Abstract

The invention provides a statistical method for accumulated working time of each stage of a turboprop engine, which comprises the following steps: acquiring flight data in real time after driving, and extracting a plurality of associated data related to the working state of an engine; calculating equivalent fuel value intervals of the engine under n working states based on the equivalent fuel value related parameters in the associated data; judging the working state of the engine at the current moment based on the equivalent fuel value interval and the instantaneous actual fuel consumption in the associated data; counting the accumulated working time of the engine in the working state, judging whether the engine is in the ground working stage or not based on the relevant parameters of the engine working stage in the associated data, and calculating the actual working time of the engine; and repeating the steps, and counting the actual working time of each working state of the engine until the engine stops. The statistical method can accurately reflect the working condition of the engine, thereby better realizing the daily maintenance/repair of the engine.

Description

Statistical method for accumulated working time of each stage of turboprop engine
Technical Field
The invention relates to the field of avionics, and designs an engine working time statistical technology, in particular to a statistical method for accumulated working time of each stage of a turboprop engine.
Background
The aircraft engine is used as a core power output component of the aircraft, and the accumulated working time of the aircraft engine is mastered to establish a flight file, realize single-machine monitoring and determine the service life of a single machine. In the flight process, the flight parameter system needs to continuously record flight data, and the whole flight process, flight accidents, equipment faults and the like are analyzed through the flight data.
At present, the accumulated working time of an aircraft engine is counted in a manual record query mode, and the problems of low working efficiency and deviation of a counting result exist.
Because the working time of the aircraft engine is different in different flight stages, the flight data values recorded at the same time are different, and the flight data contains data related to the action state of the aircraft engine, if the flight accumulated time can be calculated by using the related data, the working condition of the aircraft engine can be accurately reflected, and the routine maintenance/repair of the aircraft engine can be better realized.
Disclosure of Invention
The invention aims to design a statistical method for the accumulated working time of each stage of a turboprop engine, which is based on flight data, designs an algorithm for the accumulated working time of the engine, and accurately calculates and counts the accumulated working time of each stage of the turboprop engine, thereby achieving the purpose of monitoring the working state of the engine.
The technical scheme for realizing the purpose of the invention is as follows: a statistical method for accumulated operating time of stages of a turboprop engine, comprising the steps of:
s1, acquiring flight data in real time after the airplane is driven, and extracting and analyzing a plurality of associated data related to the working state of the engine in the flight data;
s2, calculating equivalent fuel value intervals of the engine in n working states based on the equivalent fuel value related parameters in the associated data;
s3, judging the working state of the engine at the current moment based on the equivalent fuel value interval and the instantaneous actual fuel consumption in the associated data;
s4, counting the accumulated working time of the engine in the working state of the step S3, and judging whether the engine is in the ground working stage when the engine is in the working state of the step S3 based on the relevant parameters of the working stage of the engine in the relevant data:
if the engine is in the ground working state, counting the actual working time of the engine by the a multiplied accumulated working time; if not, counting the actual working time by the b multiplied by the accumulated working time;
and S5, repeating the steps S1 to S4, and counting the actual working time of each working state of the engine until the engine stops.
The statistical method for the accumulated working time of each stage of the turboprop engine realizes the statistics of the accumulated working time of n working states of the engine by fully utilizing flight data associated with the working state of the engine so as to accurately reflect the working condition of the engine, thereby better realizing the daily maintenance/repair of the turboprop engine.
In an embodiment of the invention, the parameters related to the equivalent fuel value include engine speed, engine throttle angle PAL, instantaneous engine fuel consumption G, atmospheric static pressure PH, mach number, and total atmospheric temperature tHTotal intake pressure P of engine air inlet1。
Furthermore, the working states of the engine comprise working states corresponding to engine accelerator angle PAL within the range of PAL less than or equal to 84 and less than or equal to 100, PAL less than or equal to 84 and less than or equal to 68, PAL less than or equal to 58 and less than or equal to 50 and less than or equal to 38, PAL less than or equal to 24 and PAL less than or equal to 20 and less than or equal to 24 and PAL less than or equal to 6 and greater than or equal to 0 and less than or equal to 6 respectively.
Further, in step S3, the method for determining the operating state of the engine includes:
when the engine is defined to be in a certain working state, an engine accelerator angle PAL is k < PAL and is less than or equal to p, and an equivalent G fuel interval value [ m, n ] is calculated, wherein m corresponds to the equivalent G fuel value of the engine accelerator angle PAL which is k, and n corresponds to the equivalent G fuel value of the engine accelerator angle PAL which is p;
comparing the instantaneous actual fuel consumption in the associated data with the equivalent G fuel interval value [ m, n ], and if the instantaneous actual fuel consumption is in the range of the equivalent G fuel interval value [ m, n ], the engine is in a working state corresponding to the range of the equivalent G fuel interval value [ m, n ] at the moment; and if the instantaneous actual fuel consumption is not in the range of the equivalent G fuel interval value [ m, n ], the engine is in other working states at the moment.
Furthermore, the calculation method of the equivalent G fuel values m and n comprises the following steps:
Gfuel 1＝[1200-0.5286(760-7.5Ph)-1.5Ph(δIntake air·B-1)-△GFuel oil]·C(kg/h)；
GFuel oil 2＝15·A·δIntake air·B·PH·C(kg/h)；
GFuel oil＝GMinimum value(GFuel 1、GFuel oil 2Minimum of both) -. DELTAq takeoff·C；
Wherein, deltaIntake airThe total pressure loss coefficient of the air inlet passage of the engine is shown; b is a stamping coefficient; delta G fuel is when tH>Δ G fuel 7.5 (tH-35) at 35 ℃; when tH is less than or equal to 35 ℃, the delta G fuel oil is 0; c is an accelerator angle coefficient; a is a temperature coefficient; tH is the total atmospheric temperature; p1Total intake pressure of an engine air inlet passage;
Figure BDA0003343793870000031
in an embodiment of the present invention, the parameters related to the working phase of the engine include a left front wheel braking pressure, a left rear wheel braking pressure, a right front wheel braking pressure, and a right rear wheel braking pressure.
Further, the method for judging whether the engine is in the ground working stage comprises the following steps: and if any 2 or more pressure values in the left front airplane wheel braking pressure, the left rear airplane wheel braking pressure, the right front airplane wheel braking pressure and the right rear airplane wheel braking pressure are more than or equal to 14MPa, judging that the engine is in the ground working stage.
Further, in step S4, in the calculation of the actual engine operating time, a is 20% and b is 100%.
Compared with the prior art, the invention has the beneficial effects that: the statistical method for the accumulated working time of each stage of the turboprop engine realizes the statistics of the accumulated working time of n working states of the turboprop engine by fully utilizing flight data associated with the working states of the turboprop engine so as to accurately reflect the working condition of the turboprop engine, thereby better realizing the daily maintenance/repair of the turboprop engine.
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In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings used in the description of the embodiment will be briefly introduced below. It should be apparent that the drawings in the following description are only for illustrating the embodiments of the present invention or technical solutions in the prior art more clearly, and that other drawings can be obtained by those skilled in the art without any inventive work.
FIG. 1 is a flow chart of a statistical method of accumulated operating time for various stages of a turboprop engine in accordance with an embodiment.
Detailed Description
The invention will be further described with reference to specific embodiments, and the advantages and features of the invention will become apparent as the description proceeds. These examples are illustrative only and do not limit the scope of the present invention in any way. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention, and that such changes and modifications may be made without departing from the spirit and scope of the invention.
In the description of the present embodiments, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The specific embodiment provides a statistical method for accumulated working time of each stage of a turboprop engine, which comprises the following steps:
and S1, acquiring flight data in real time after the airplane is driven, and extracting and analyzing a plurality of associated data related to the working state of the engine in the flight data.
Specifically, the plurality of associated data related to the engine operating state includes equivalent fuel value related parameters, instantaneous actual fuel consumption, and engine operating stage related parameters. The parameters related to the equivalent fuel value comprise the engine speed, the engine throttle angle PAL, the instantaneous fuel consumption G of the engine, the atmospheric static pressure PH, the Mach number and the atmospheric total temperature tHTotal intake pressure P of engine air inlet1(ii) a The relevant parameters of the working stage of the engine comprise the brake pressure of a left front airplane wheel, the brake pressure of a left rear airplane wheel, the brake pressure of a right front airplane wheel and the brake pressure of a right rear airplane wheel.
And S2, calculating equivalent fuel value intervals of the engine under n working states based on the equivalent fuel value related parameters in the associated data.
Specifically, the working states of the engine comprise working states corresponding to engine accelerator angle PAL within the range of PAL being more than 84 and less than or equal to 100, PAL being more than 68 and less than or equal to 84, PAL being more than 58 and less than or equal to 68, PAL being more than 50 and less than or equal to 58, PAL being more than 38 and less than or equal to 50, PAL being more than or equal to 24, PAL being more than or equal to 20 and less than or equal to 24, PAL being more than or equal to 0 and less than or equal to 6. Wherein, PAL more than 84 and less than or equal to 100 corresponds to the takeoff state of the engine; 68 < PAL ≦ 84 corresponds to the rated state of the engine; PAL is more than 58 and less than or equal to 68, which corresponds to the rated state of 0.85 of the airplane; PAL is more than 50 and less than or equal to 58, which corresponds to the 0.7 rated state of the engine; PAL more than 38 and less than or equal to 50 corresponds to the 0.6 rated state of the engine; PAL is more than 24 and less than or equal to 38, which corresponds to the 0.4 rated state of the engine; PAL is more than or equal to 20 and less than or equal to 24, which corresponds to the 0.2 rated state of the engine; PAL more than 0 and less than or equal to 6 is corresponding to the slow-moving state of the engine.
Specifically, the method for judging the operating state of the engine comprises the following steps: when the engine is defined to be in a certain working state, an engine accelerator angle PAL is k < PAL and is less than or equal to p, and an equivalent G fuel interval value [ m, n ] is calculated, wherein m corresponds to the equivalent G fuel value of the engine accelerator angle PAL which is k, and n corresponds to the equivalent G fuel value of the engine accelerator angle PAL which is p;
comparing the instantaneous actual fuel consumption in the associated data with the equivalent G fuel interval value [ m, n ], and if the instantaneous actual fuel consumption is in the range of the equivalent G fuel interval value [ m, n ], the engine is in a working state corresponding to the range of the equivalent G fuel interval value [ m, n ] at the moment; and if the instantaneous actual fuel consumption is not in the range of the equivalent G fuel interval value [ m, n ], the engine is in other working states at the moment.
The calculation method of the equivalent G fuel values m and n comprises the following steps:
Gfuel 1＝[1200-0.5286(760-7.5Ph)-1.5Ph(δIntake air·B-1)-△GFuel oil]·C(kg/h)；
GFuel oil 2＝15·A·δIntake air·B·PH·C(kg/h)；
GFuel oil＝GMinimum value(GFuel 1、GFuel oil 2Minimum of both) -. DELTAq takeoff·C；
Wherein, deltaIntake airThe total pressure loss coefficient of the air inlet passage of the engine is shown; b is a stamping coefficient; delta G fuel is when tH>Δ G fuel 7.5 (tH-35) at 35 ℃; when tH is less than or equal to 35 DEG CWhen the fuel oil delta G is equal to 0; c is an accelerator angle coefficient; a is a temperature coefficient; tH is the total atmospheric temperature; p1Total intake pressure of an engine air inlet passage;
Figure BDA0003343793870000061
and S3, judging the working state of the engine at the current moment based on the equivalent fuel value interval and the instantaneous actual fuel consumption in the associated data.
Specifically, the engine throttle angle PAL is explained in the range of 68 < PAL ≦ 84, and the equivalent G fuel values (i.e. m and n mentioned in step S2) of the engine throttle angle PAL at 68 ° and 84 ° at the current moment are respectively calculated through the data extracted in step S1; the instantaneous actual fuel consumption extracted at the current moment and the calculated equivalent G fuel values of PAL at 68 DEG and 84 DEG are compared, when the instantaneous actual fuel consumption is between the two values, the rated state of the engine corresponding to the current moment that PAL is more than 68 and less than or equal to 84 is judged, and the current moment is counted into the accumulated working time of the rated state statistics; and when the instantaneous actual fuel consumption is out of the two values, judging that the engine is in other working states at the current moment, and counting the moment into the accumulated working time counted by the other working states.
S4, counting the accumulated working time of the engine in the working state of the step S3, and judging whether the engine is in the ground working stage when the engine is in the working state of the step S3 based on the relevant parameters of the working stage of the engine in the relevant data:
if the engine is in the ground working state, counting the actual working time of the engine by the a multiplied accumulated working time; if not, the actual working time is counted as b multiplied by the accumulated working time.
Specifically, the method for judging whether the engine is in the ground working stage comprises the following steps: and if any 2 or more pressure values in the left front airplane wheel braking pressure, the left rear airplane wheel braking pressure, the right front airplane wheel braking pressure and the right rear airplane wheel braking pressure are more than or equal to 14MPa, judging that the engine is in the ground working stage.
Preferably, since the consumption of the engine is different between the ground operation phase and the other operation phases, in the present embodiment, in the calculation of the actual operation time of the engine, a is 20%, and b is 100%, that is, if the engine is in the ground operation phase, the actual operation time of the engine is counted by 20% of the accumulated operation time; if the engine is in other stages, the actual working time of the engine is counted by 100% of the accumulated working time.
And S5, repeating the steps S1 to S4, and counting the actual working time of each working state of the engine until the engine stops.
Through the method of the invention, the actual working time of 8 working states of the engine is counted and then is reflected in an EXCEL table, the EXCEL table comprises associated data related to the working state of the engine, the flight parameter recording time length, the accumulated working time of each working stage of the engine and the total accumulated working time of the engine, and the flow of the method for counting the accumulated working time of each stage of the turboprop engine is shown in figure 1.
The statistical method for the accumulated working time of each stage of the turboprop engine realizes the statistics of the accumulated working time of n working states of the engine by fully utilizing flight data associated with the working state of the engine so as to accurately reflect the working condition of the engine, thereby better realizing the daily maintenance/repair of the turboprop engine.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims (8)

1. A statistical method for accumulated operating time of various stages of a turboprop engine, comprising the steps of:
s1, acquiring flight data in real time after the airplane is driven, and extracting and analyzing a plurality of associated data related to the working state of the engine in the flight data;
s2, calculating equivalent fuel value intervals of the engine in n working states based on the equivalent fuel value related parameters in the associated data;
s3, judging the working state of the engine at the current moment based on the equivalent fuel value interval and the instantaneous actual fuel consumption in the associated data;
s4, counting the accumulated working time of the engine in the working state of the step S3, and judging whether the engine is in the ground working stage when the engine is in the working state of the step S3 based on the relevant parameters of the working stage of the engine in the relevant data:
if the engine is in the ground working state, counting the actual working time of the engine by the a multiplied accumulated working time; if not, counting the actual working time by the b multiplied by the accumulated working time;
and S5, repeating the steps S1 to S4, and counting the actual working time of each working state of the engine until the engine stops.
2. The statistical method for cumulative operating times for each stage of a turboprop according to claim 1, characterized in that: the parameters related to the equivalent fuel value comprise the engine speed, the engine throttle angle PAL, the instantaneous fuel consumption G of the engine, the atmospheric static pressure PH, the Mach number and the atmospheric total temperature tHTotal intake pressure P of engine air inlet1。
3. The statistical method for cumulative operating times for each stage of a turboprop according to claim 2, characterized in that: the working state of the engine comprises the working states of the engine accelerator angle PAL in the range of PAL more than 84 and less than or equal to 100, PAL more than 68 and less than or equal to 84, PAL more than 58 and less than or equal to 68, PAL more than 50 and less than or equal to 58, PAL more than 38 and less than or equal to 50, PAL more than 24 and less than or equal to 38, PAL more than or equal to 20 and less than or equal to 24 and PAL more than 0 and less than or equal to 6 respectively.
4. The statistical method for cumulative operating times for each stage of a turboprop according to claim 3, characterized in that: in step S3, the method for determining the operating state of the engine includes:
when the engine is defined to be in a certain working state, an engine accelerator angle PAL is k < PAL and is less than or equal to p, and an equivalent G fuel interval value [ m, n ] is calculated, wherein m corresponds to the equivalent G fuel value of the engine accelerator angle PAL which is k, and n corresponds to the equivalent G fuel value of the engine accelerator angle PAL which is p;
comparing the instantaneous actual fuel consumption in the associated data with the equivalent G fuel interval value [ m, n ], and if the instantaneous actual fuel consumption is in the range of the equivalent G fuel interval value [ m, n ], the engine is in a working state corresponding to the range of the equivalent G fuel interval value [ m, n ] at the moment; and if the instantaneous actual fuel consumption is not in the range of the equivalent G fuel interval value [ m, n ], the engine is in other working states at the moment.
5. The statistical method for cumulative operating times at various stages of a turbo-engine according to claim 4, characterized in that the equivalent G fuel values m and n are calculated by:
Gfuel 1＝[1200-0.5286(760-7.5Ph)-1.5Ph(δIntake air·B-1)-△GFuel oil]·C(kg/h)；
GFuel oil 2＝15·A·δIntake air·B·PH·C(kg/h)；
GFuel oil＝GMinimum value(GFuel 1、GFuel oil 2Minimum of both) -. DELTAq takeoff·C；
Wherein, deltaIntake airThe total pressure loss coefficient of the air inlet passage of the engine is shown; b is a stamping coefficient; delta G fuel is when tH>Δ G fuel 7.5 (tH-35) at 35 ℃; when tH is less than or equal to 35 ℃, the delta G fuel oil is 0; c is an accelerator angle coefficient; a is a temperature coefficient; tH is the total atmospheric temperature; p1Total intake pressure of an engine air inlet passage;
Figure FDA0003343793860000021
6. the statistical method for cumulative operating times for each stage of a turboprop according to claim 1, characterized in that: the relevant parameters of the working stage of the engine comprise the brake pressure of a left front airplane wheel, the brake pressure of a left rear airplane wheel, the brake pressure of a right front airplane wheel and the brake pressure of a right rear airplane wheel.
7. The statistical method for accumulated operating time of each stage of a turbo-propeller engine as set forth in claim 6, wherein the method for determining whether the engine is in the ground operating stage is: and if any 2 or more pressure values in the left front airplane wheel braking pressure, the left rear airplane wheel braking pressure, the right front airplane wheel braking pressure and the right rear airplane wheel braking pressure are more than or equal to 14MPa, judging that the engine is in the ground working stage.
8. The statistical method for the cumulative operating time of each stage of the turbo engine according to claim 6 or 7, wherein in step S4, a is 20% and b is 100%.
CN202111318517.1A 2021-11-08 2021-11-08 Statistical method for accumulated working time of each stage of turboprop engine Pending CN114116833A (en)

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