CN115342771A - Method for calibrating throat area of adjustable circular tail nozzle of aircraft engine - Google Patents

Method for calibrating throat area of adjustable circular tail nozzle of aircraft engine Download PDF

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Publication number
CN115342771A
CN115342771A CN202210982352.6A CN202210982352A CN115342771A CN 115342771 A CN115342771 A CN 115342771A CN 202210982352 A CN202210982352 A CN 202210982352A CN 115342771 A CN115342771 A CN 115342771A
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Prior art keywords
throat
tail
area
nozzle
detected
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Inventor
颜荣
段发阶
王泽莉
谷东格
樊金侠
李友江
傅骁
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Tianjin University
AECC Sichuan Gas Turbine Research Institute
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Tianjin University
AECC Sichuan Gas Turbine Research Institute
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Priority to CN202210982352.6A priority Critical patent/CN115342771A/en
Publication of CN115342771A publication Critical patent/CN115342771A/en
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • G01B21/28—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring areas
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/26—Measuring arrangements characterised by the use of mechanical techniques for measuring areas, e.g. planimeters
    • 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
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Engines (AREA)

Abstract

The invention discloses a method for calibrating the throat area of an adjustable circular tail nozzle of an aircraft engine, which comprises the following steps: analyzing the detection requirement; cleaning the part to be detected; marking the detection location; the contraction and expansion state is stably checked, and the throat part of the tail nozzle to be detected is ensured not to have the clamping stagnation problem; detecting the size of the throat part of the tail nozzle to be detected in each state; calculating the throat area of the tail nozzle to be measured in each state; establishing a calibration model of the throat area of the exhaust nozzle to be measured, and utilizing the calculated value S of the throat area of the exhaust nozzle to be measured in each state based on the least square method i And a control signal value V i Establishing an area calibration model according to needs, and solving a fitting coefficient; based on the established area calibration model, the calibration result is checked; and (4) providing a calibration report and tidying the test site.

Description

Method for calibrating throat area of adjustable circular tail nozzle of aircraft engine
Technical Field
The invention belongs to the field of metering and detecting of aero-engines, and particularly relates to a method for calibrating the throat area of an adjustable circular exhaust nozzle of an aero-engine.
Background
Modern aircraft engines are developing towards high thrust-weight ratio, high pressure ratio, high temperature before vortex and high maneuverability, and particularly, a new generation of variable cycle engine is taken as a representative, and the thrust and the lift of the engine reach a new height. The tail nozzle is a key part for generating thrust and lift force of the aircraft engine, and has the structural characteristics that the tail nozzle is matched with a flow channel of an aircraft and is highly integrated with a machine body, and the size and the direction of the generated thrust have decisive influence on the performance of the aircraft engine. Researches show that the initial expansion angle, the total length, the area expansion ratio, the length of the outer cover, the expansion angle of the inner wall of the outer cover and other geometric parameters of the tail nozzle have important influence on the performance of the tail nozzle, wherein the throat area of the tail nozzle is directly related to the expansion degree of airflow in the outer nozzle, so that the thrust coefficient, the lift coefficient and the pitching moment coefficient are influenced.
Along with the continuous improvement of the requirements on the maneuvering performance of the airplane, more and more high-performance aircraft engines adopt the adjustable tail nozzle to replace the traditional fixed tail nozzle, and the throat area of the tail nozzle can be changed according to engine control signals by the unique structure of the adjustable tail nozzle, so that the regulation and control of the performances of the engine such as thrust, lift force and the like under different rotating speed working conditions are realized. However, in order to ensure accurate and reliable engine performance control, the throat area of the adjustable exhaust nozzle must be calibrated before a test, and the control signals are ensured to be in one-to-one correspondence with the throat area. In addition, in the engine development stage, due to the fact that repeated assembly and disassembly of a mechanical structure can cause slight changes of calibration parameters, the throat area of the tail nozzle needs to be calibrated again before each complete machine test. Therefore, the calibration of the throat area of the adjustable tail nozzle of the aircraft engine is a necessary link for guaranteeing the performance of the engine and ensuring the smooth development of the test.
Currently, the adjustable exhaust nozzles are divided into circular exhaust nozzles and rectangular exhaust nozzles, wherein the circular exhaust nozzles are most widely applied, and the special sealing sheet and adjusting sheet alternate laminated structure of the circular exhaust nozzles provides great challenges for calibration technology.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a method for calibrating the throat area of an adjustable circular tail nozzle of an aero-engine.
The purpose of the invention is realized by the following technical scheme:
a method for calibrating the throat area of an adjustable circular tail nozzle of an aircraft engine comprises the following steps:
s1, analyzing the detection requirement, and selecting a measuring tool according to the change range of the throat diameter of the tail nozzle to be measured and the measurement precision requirement;
s2, cleaning the part to be detected, and cleaning oil stains on the surfaces of a sealing sheet and an adjusting sheet of the throat part of the tail spray pipe to be detected;
s3, marking the detection position, carrying out coding marking on sealing pieces and adjusting pieces of the throat part of the tail nozzle to be detected, wherein a pair of sealing pieces or adjusting pieces at the relative position of the throat part are 1 group, marking m groups of sealing pieces and m groups of adjusting pieces in total, and taking m to be more than or equal to 3;
s4, stably checking a contraction and expansion state, controlling the contraction and expansion of the throat part of the tail nozzle to be detected through the oil source vehicle, checking whether the contraction and expansion process is smooth or not, and ensuring that the throat part of the tail nozzle to be detected does not have the clamping stagnation problem;
s5, detecting the size of the throat part of the tail spray pipe to be detected in each state, and setting the throat part of the tail spray pipe to be detectedThe section area from the maximum to the minimum is divided into N states, N is more than or equal to 5, the throat part of the tail spray pipe to be measured is controlled to be adjusted to different states i according to the sequence from large to small, the distance between two sealing sheets in each group of sealing sheets is detected by using a measuring tool and recorded as D i1 ,D i2 ,......,D im And the distance between two adjusting sheets in each group of adjusting sheets is recorded as D' i1 ,D' i2 ,......,D' im Recording the control signal value V in the corresponding state i (ii) a The control signal value is the angular displacement sensor difference ratio and the signal value;
s6, calculating the throat area of the tail nozzle to be measured in each state;
s7, establishing a calibration model of the throat area of the tail nozzle to be measured, and based on a least square method, utilizing the calculated value S of the throat area of the tail nozzle to be measured in each state i And a control signal value V i Establishing an area calibration model according to needs, and solving a fitting coefficient;
s8, based on the area calibration model established in the S7 step, a calibration result is checked, the sizes of the throats of the tail nozzles in other M states are detected according to the methods of the S5 step and the S6 step, M is larger than or equal to 3, the M states are not coincident with the N states in the S5 step, the observed values S 'of the throats of the tail nozzles to be detected and the observed values V' of the control signals are obtained, the data of the maximum state and the minimum state are removed, the observed values of the control signals in the rest M-2 states are substituted into the area calibration model, and the estimated values of the throats of the tail nozzles to be detected M-2 are obtained through calculation
Figure BDA0003800612430000021
Comparing the estimated value with the observed value V', if the error meets the requirement, carrying out the next step, otherwise returning to the step S3, and carrying out calibration again;
and S9, issuing a calibration report and finishing a test site.
Further, in step S6, assuming that the throat of the exhaust nozzle to be measured is formed by splicing n sealing pieces and n adjusting pieces, the area of the polygon is regarded as the superposition of the areas of 2n triangles including the n sealing piece triangles and the n adjusting piece triangles, so that the area of the polygon in a certain state i is calculated as
Figure BDA0003800612430000031
Wherein W is the width of the sealing sheet, theta is the included angle between the sealing sheet and the adjusting sheet, alpha is 1/2 of the triangle apex angle of the sealing sheet,
Figure BDA0003800612430000032
is the average distance between the sealing sheets,
Figure BDA0003800612430000033
the average distance between the flaps is adjusted.
Further, in the area calibration model, the input quantity is a control signal value V, and the output quantity is an estimated value of the throat area
Figure BDA0003800612430000034
The two should be in accordance with:
Figure BDA0003800612430000035
in the formula (I), the compound is shown in the specification,
Figure BDA0003800612430000036
is a fitting coefficient estimated value; according to the least square method, the size of the throat part of the exhaust nozzle to be detected and the control signal value which are obtained by detection in the step S5 are utilized, and the fitting coefficient is estimated to be
Figure BDA0003800612430000037
In the formula, S i 、V i And N is the number of states, wherein N is the observed value of the throat area of the tail nozzle to be detected and the control signal in each state.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
the method realizes the accurate calibration of the throat area of the adjustable circular jet pipe of the aero-engine by marking the detection position, detecting the throat size of the jet pipe to be detected in each state, calculating the throat area of the jet pipe to be detected, constructing an area calibration model, solving parameters and checking a calibration result. For a new generation of aero-engine, the adjustable tail nozzle is a key part for determining performance exertion, the invention provides an effective method and a complete process for calibrating the throat area of the adjustable circular tail nozzle, comprehensively considers the actual engineering field, can effectively reduce the measurement uncertainty introduced by the factors such as subjective experience of operators, mechanical return error, calculation formula difference and the like, realizes the rapid and accurate calibration of the throat area of the adjustable circular tail nozzle, improves the whole machine test efficiency of the aero-engine, and lays a foundation for finally forming the test specification of the aero-engine.
Drawings
FIG. 1 is a flow chart of a method for calibrating the throat area of an adjustable circular jet nozzle of an aircraft engine.
FIG. 2 is a schematic view of the adjustable circular jet nozzle throat marker detection position of the present invention.
FIG. 3 is a schematic diagram of the calculation of the throat area of the variable circular jet nozzle of the present invention.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides a method for calibrating the throat area of an adjustable circular exhaust nozzle of an aircraft engine, which mainly comprises the following steps as shown in figure 1:
s1, analyzing and detecting requirements, and reasonably selecting a measuring tool such as an internal micrometer or other automatic measuring devices according to the change range of the throat diameter of the tail nozzle to be measured and the measurement precision requirement.
And S2, cleaning the part to be measured, cleaning oil stains and the like on the surfaces of the sealing sheet and the adjusting sheet of the throat part of the tail spray pipe to be measured, and preventing pollutants from influencing the measurement result.
And S3, marking the detection position, and carrying out coding marking on the sealing plate and the adjusting plate of the throat of the tail nozzle to be detected, wherein as shown in figure 2, a pair of sealing plates or adjusting plates at the relative position of the throat is 1 group, and 3 groups of sealing plates (1 #,2#,3 #) and 3 groups of adjusting plates (1 ' #,2' #,3' #) are marked in total.
S4, stably checking a contraction and expansion state, controlling the contraction and expansion of the throat part of the tail jet pipe to be detected through the oil source vehicle, checking whether the contraction and expansion process is smooth, and ensuring that the throat part of the tail jet pipe to be detected does not have the clamping stagnation problem.
S5, detecting the throat size of the exhaust nozzle to be detected in each state, setting the sectional area of the throat of the exhaust nozzle from the maximum to the minimum to be N =5 states, controlling the exhaust nozzle to be adjusted to different states i, i is less than or equal to N, and detecting the distance (marked as D) between two sealing sheets in each group of sealing sheets by using a measuring tool in order of strictly from large to small to eliminate return error and ensure measuring precision i1 ,D i2 ,D i3 ) And the distance (denoted as D ') between the two adjusting sheets in each group of adjusting sheets' i1 ,D' i2 ,D' i3 ) As shown in FIG. 3, the control signal value V (typically, the angular displacement sensor difference ratio and the signal value) in this state is recorded i 。
S6, calculating the throat area of the exhaust nozzle to be measured in each state, and calculating the throat area of each state, wherein the throat area of the exhaust nozzle needs to be particularly noticed, although the throat of the exhaust nozzle is approximately circular, the throat area of the exhaust nozzle is actually a polygon formed by splicing a plurality of sealing sheets and adjusting sheets, and therefore specific analysis is needed:
as shown in fig. 3, assuming that the throat of the exhaust nozzle to be measured is formed by splicing 8 sealing pieces and 8 adjusting pieces, the area of the polygon can be regarded as the superposition of the areas of 2 × 8 triangles (including 8 sealing piece triangles and 8 adjusting piece triangles), so that the area of the polygon in a certain state i can be calculated as
Figure BDA0003800612430000051
Wherein W is the width of the sealing sheet, theta is the included angle between the sealing sheet and the adjusting sheet, alpha is 1/2 of the triangular vertex angle of the sealing sheet,
Figure BDA0003800612430000052
is the average distance between the sealing sheets,
Figure BDA0003800612430000053
to adjust the average distance between the blades.
S7, establishing a calibration model of the throat area of the tail nozzle to be measured, and utilizing the calculated value S of the throat area in each state based on a least square method i And a control signal value V i Establishing an area calibration model, wherein the input quantity is a control signal value V and the output quantity is a throat area estimation value
Figure BDA0003800612430000054
The two should meet:
Figure BDA0003800612430000055
in the formula (I), the compound is shown in the specification,
Figure BDA0003800612430000056
are fitting coefficient estimates. Estimating a fitting coefficient of using the throat size value and the control signal value detected in step S5 according to a least square method
Figure BDA0003800612430000057
In the formula, S i 、V i And (4) observing the area of the throat of the tail spray pipe and the control signal under each state.
S8, testing a calibration result, testing the calibration result based on the area calibration model established in the step S7, detecting the throat size of the exhaust nozzle to be tested in other 3 states according to the methods in the steps S5 and S6, obtaining an observed value S 'of the 3 throat areas and an observed value V' of the control signal, removing data of the maximum state and the minimum state, substituting the observed values of the control signal in the rest 1 state into a formula (2), and calculating to obtain an estimated value of the 1 throat area
Figure BDA0003800612430000058
Will estimate the value
Figure BDA0003800612430000059
And comparing the error with the observed value V', if the error meets the requirement, carrying out the next step, otherwise, returning to the step S3, and carrying out calibration again.
And S9, issuing a calibration report and arranging the test site.
Finally, it should be pointed out that: the above examples are intended to illustrate the computational process of the present invention, and are not intended to be limiting thereof. Although the present invention has been described in detail with reference to the foregoing examples, those skilled in the art will appreciate that the computing processes described in the foregoing examples can be modified or equivalent substituted for some of the parameters without departing from the spirit and scope of the computing method.
The present invention is not limited to the embodiments described above. The foregoing description of the specific embodiments is intended to describe and illustrate the technical solutions of the present invention, and the above specific embodiments are merely illustrative and not restrictive. Those skilled in the art can make many changes and modifications to the invention without departing from the spirit and scope of the invention as defined in the appended claims.

Claims (3)

1. A method for calibrating the throat area of an adjustable circular tail nozzle of an aircraft engine is characterized by comprising the following steps:
s1, analyzing the detection requirement, and selecting a measuring tool according to the change range of the throat diameter of the tail nozzle to be measured and the measurement precision requirement;
s2, cleaning the part to be measured, and cleaning oil stains on the surfaces of a sealing sheet and an adjusting sheet of the throat part of the tail spray pipe to be measured;
s3, marking the detection position, coding and marking sealing pieces and adjusting pieces of the throat part of the tail nozzle to be detected, wherein a pair of sealing pieces or adjusting pieces at the relative position of the throat part are 1 group, marking m groups of sealing pieces and m groups of adjusting pieces totally, and taking m to be more than or equal to 3;
s4, stably checking a contraction and expansion state, controlling the contraction and expansion of the throat part of the tail spray pipe to be tested through the oil source vehicle, checking whether the contraction and expansion process is smooth, and ensuring that the throat part of the tail spray pipe to be tested does not have the clamping stagnation problem;
s5, detecting the size of the throat part of the tail spray pipe to be detected in each state, setting the maximum-minimum segmentation of the throat area of the tail spray pipe to be detected as N states, wherein N is more than or equal to 5, controlling the throat part of the tail spray pipe to be detected to be adjusted to different states i according to the sequence from large to small, detecting the distance between two sealing pieces in each group of sealing pieces by using a measuring tool and recording the distance as D i1 ,D i2 ,......,D im And the distance between two adjusting sheets in each group of adjusting sheets is recorded as D' i1 ,D' i2 ,......,D' im Recording the control signal value V in the corresponding state i (ii) a The control signal value is the angular displacement sensor difference ratio and the signal value;
s6, calculating the throat area of the tail nozzle to be measured in each state;
s7, establishing a calibration model of the throat area of the tail nozzle to be measured, and based on a least square method, utilizing the calculated value S of the throat area of the tail nozzle to be measured in each state i And a control signal value V i Establishing an area calibration model according to needs, and solving a fitting coefficient;
s8, based on the area calibration model established in the S7 step, a calibration result is checked, the sizes of the throats of the tail nozzles in other M states are detected according to the methods of the S5 step and the S6 step, M is larger than or equal to 3, the M states are not coincident with the N states in the S5 step, the observed values S 'of the throats of the tail nozzles to be detected and the observed values V' of the control signals are obtained, the data of the maximum state and the minimum state are removed, the observed values of the control signals in the rest M-2 states are substituted into the area calibration model, and the estimated values of the throats of the tail nozzles to be detected M-2 are obtained through calculation
Figure FDA0003800612420000011
Comparing the estimated value with the observed value V', if the error meets the requirement, carrying out the next step, otherwise returning to the step S3, and carrying out calibration again;
and S9, issuing a calibration report and finishing a test site.
2. The method for calibrating the throat area of the adjustable circular jet nozzle of the aircraft engine according to claim 1, wherein in the step S6, assuming that the throat of the jet nozzle to be measured is formed by splicing n sealing pieces and n adjusting pieces, the polygonal area is regarded as the superposition of the areas of 2n triangles including the triangles with the n sealing pieces and the triangles with the n adjusting pieces, so that the polygonal area under a certain state i is calculated as
Figure FDA0003800612420000021
Wherein W is the width of the sealing sheet, theta is the included angle between the sealing sheet and the adjusting sheet, alpha is 1/2 of the triangular vertex angle of the sealing sheet,
Figure FDA0003800612420000022
is the average distance between the sealing sheets and,
Figure FDA0003800612420000023
the average distance between the flaps is adjusted.
3. The method for calibrating the throat area of the circular adjustable jet nozzle of an aircraft engine as claimed in claim 1, wherein in the area calibration model, the input quantity is a control signal value V, and the output quantity is an estimated value of the throat area
Figure FDA0003800612420000024
The two should be in accordance with:
Figure FDA0003800612420000025
in the formula (I), the compound is shown in the specification,
Figure FDA0003800612420000026
is a fitting coefficient estimated value; according to the least square method, the size sum of the throat part of the exhaust nozzle to be detected is obtained by utilizing the detection in the step S5Control signal values, estimating fitting coefficients as
Figure FDA0003800612420000027
In the formula, S i 、V i And N is the number of states, wherein N is the observed value of the throat area of the tail nozzle to be detected and the control signal in each state.
CN202210982352.6A 2022-08-16 2022-08-16 Method for calibrating throat area of adjustable circular tail nozzle of aircraft engine Pending CN115342771A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118089606A (en) * 2024-04-29 2024-05-28 山东中玮动力科技有限公司 Tail nozzle testing system for aeroengine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118089606A (en) * 2024-04-29 2024-05-28 山东中玮动力科技有限公司 Tail nozzle testing system for aeroengine
CN118089606B (en) * 2024-04-29 2024-07-09 山东中玮动力科技有限公司 Tail nozzle testing system for aeroengine

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