WO2019109241A1 - 将内窥检查的数据进行记录的方法和系统 - Google Patents

将内窥检查的数据进行记录的方法和系统 Download PDF

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Publication number
WO2019109241A1
WO2019109241A1 PCT/CN2017/114583 CN2017114583W WO2019109241A1 WO 2019109241 A1 WO2019109241 A1 WO 2019109241A1 CN 2017114583 W CN2017114583 W CN 2017114583W WO 2019109241 A1 WO2019109241 A1 WO 2019109241A1
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Prior art keywords
damage
data
component
inspection
template
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PCT/CN2017/114583
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English (en)
French (fr)
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程琳
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程琳
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Priority to PCT/CN2017/114583 priority Critical patent/WO2019109241A1/zh
Priority to US16/063,966 priority patent/US11120651B2/en
Priority to CN201780044509.8A priority patent/CN109791567B/zh
Publication of WO2019109241A1 publication Critical patent/WO2019109241A1/zh

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    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
    • G07C5/0841—Registering performance data
    • G07C5/085—Registering performance data using electronic data carriers
    • G07C5/0866—Registering performance data using electronic data carriers the electronic data carrier being a digital video recorder in combination with video camera
    • 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
    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
    • G02B23/24—Instruments or systems for viewing the inside of hollow bodies, e.g. fibrescopes
    • G02B23/2476—Non-optical details, e.g. housings, mountings, supports
    • G02B23/2484—Arrangements in relation to a camera or imaging device
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
    • G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
    • G06F16/22—Indexing; Data structures therefor; Storage structures
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/008—Registering or indicating the working of vehicles communicating information to a remotely located station
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
    • G07C5/0808—Diagnosing performance data
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C2205/00—Indexing scheme relating to group G07C5/00
    • G07C2205/02—Indexing scheme relating to group G07C5/00 using a vehicle scan tool

Definitions

  • the present invention relates to the field of data processing, and in particular, to a method and system for recording endoscopically examined data.
  • the aero engine is a highly complex and sophisticated thermal machine that provides the aircraft with the power it needs to fly.
  • Modern aero-engines pursue high power-to-mass ratio, high-pressure gas ratio, and the temperature before the turbine is getting higher and higher; the engine, especially the core machine, works under high temperature, high pressure and high load environment, and the damage and expansion of engine components directly affect the safety of the aircraft. Sex and reliability.
  • the present invention provides the following technical solutions:
  • a method for recording data for endoscopic examination wherein the endoscopic examination is to check whether a device is damaged by an endoscope, and the device is composed of components, including:
  • the component hierarchy includes two levels of a unit body and a component, and the unit body includes one or more components;
  • the defining a general description template of the damage comprises: defining the damage that may occur on the component, and defining the universal description template.
  • the universal description template includes three parts: qualitative, positioning and quantitative, the qualitative means defining the damage, and the positioning means determining the position of the component where the damage is located, Quantification refers to the definition of the size of the lesion.
  • the qualitative means that the damage is defined in a manner of a main type, an auxiliary type, and a supplementary description, the main type including different subtypes.
  • the positioning refers to determining the position of the component in which the damage is located in a first position - a second position - orientation.
  • the evaluation template includes: a damage inspection result, a suggestion, and a damage development trend.
  • the damage inspection result includes:
  • the damage condition of the component is complicated, and the corresponding conclusion cannot be given according to the standard.
  • the inspection result is to be determined, and the inspection result needs to be further determined with the manufacturer of the device.
  • the suggestions include: the number of hours and/or cycles of the next repeated check, the number of hours issued by the deadline, and/or the number of cycles.
  • the trend of the damage development includes: newly discovered damage, damage unexpanded, and damage spread.
  • the evaluation template further includes: a reference basis and a supplementary explanation.
  • the defining the unit body damage summary template comprises: defining a main type of damage to be summarized, defining a subtype of the damage, and defining a size of the damage.
  • the data of the standardized entry of the endoscopic examination includes:
  • the data of the standardized entry of the endoscope inspection further includes:
  • the inspection result of all the components in the unit body is normal, and the inspection result of automatically generating the unit body is normal;
  • the method further includes: data verification, where the data verification includes:
  • the search finds that the damage description of the engine in the part already exists in the database, and the entry page prompts the entry personnel to damage the result of the last endoscopic examination of the part, and the entry person can click to view the details of the last endoscopic examination to better Judge the damage;
  • ⁇ refers to the error threshold allowed for damage measurement, generally ranging from -8% to -5%;
  • the repeated inspection interval recommended in the endoscopy inspection conclusion is compared with the last inspection result. If the recommended repeated inspection interval entered in this inspection is greater than the repeated inspection interval input last time, the worker is reminded to suggest that This repeated inspection interval conclusion is verified.
  • the above method further comprising: data storage, the data including a photograph taken when the endoscope detects the damage of the device, the photograph being an original photograph or a compressed photograph.
  • the invention also discloses a system for recording data of endoscopic examination, wherein the endoscopic examination is to check whether a device is damaged by an endoscope, the device is composed of components, and the system comprises:
  • a component hierarchy module for constructing a component hierarchy of the device, the component hierarchy comprising two levels of a unit body and a component, the unit body comprising one or more components;
  • the universal description template includes three parts: qualitative, positioning and quantitative.
  • An evaluation module including an evaluation template, for recording the inspection result of the component. If the component inspection result finds damage, the evaluation template needs to record the following information: damage inspection result, suggestion and damage development trend;
  • a unit damage summary module for summarizing the unit body damage to define a unit body damage summary template, wherein the unit damage summary template includes: defining a main type and definition of the damage to be summarized. The subtype of damage and the size of the damage defined;
  • An endoscopic examination result standardized input module for standardizing data entered into the endoscopic examination, the data of the endoscopic examination includes:
  • a data verification module configured to verify the entered data, and compare the data of the endoscopic examination entered with the historical data in the database
  • a data storage module configured to store the entered data, the data includes a photo taken when an endoscope detects a damage to the device, and the photo is an original photo or a compressed photo;
  • a record presentation module for presenting the previously entered data when it is needed for review.
  • the method and system for recording the data of the endoscopic examination disclosed in the present invention mainly achieve the following technical effects: the method of the present invention can be directly applied to the operating system of the endoscope device, and the endoscope inspection Direct report production; can also be used as an independent data collection software for workers to complete the standardized entry of endoscopy results on a computer or tablet.
  • the standardized entry of endoscopic examination results provides a continuous and stable data source for the study of the development trend of endoscopic examination component damage, damage image recognition and endoscopic examination interval research. Based on the method, the overall development trend of internal damage can be quantified, which provides a good measure for improving the reliability of modular mechanical products.
  • a method and system for recording data of endoscopic inspection which can standardize storage of images, videos, and characters damaged by internal components and components of an aeroengine or a gas turbine.
  • a method for recording data for endoscopic examination wherein the endoscopic examination is to check whether a device is damaged by an endoscope, and the device is composed of components, and the method comprises the following steps:
  • Step 1 Build the component hierarchy of the device.
  • the component hierarchy may in turn comprise two levels of a unit body and a component, the unit body comprising one or more components.
  • a module may include a sub-module, and a component may include a sub-part, a unit body, a sub-unit body, a component, and a sub-component in four levels, which includes Relationship is: unit body Subunit component Subcomponent.
  • the engine consists of five modules: a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure turbine.
  • the specific design and construction of different types of engines are not identical, so a common standardized approach is needed to establish a hierarchy for each type of engine.
  • the component hierarchy of the endoscope inspection of the engine from the module to the sub-part is constructed according to the description of the engine endoscopic inspection in the maintenance manual (AMM) of each aircraft.
  • Modules include: LPC (Low Pressure Compressor, Low Pressure Compressor), HPC (High Pressure Compressor, High Pressure Compressor), CC (Combustion Chamber, Combustion Chamber), HPT (High Pressure Turbine, High Pressure) Turbine), HPTN (High Pressure Turbine Nozzle Guide Vine, high pressure turbine guide vane), LPT (Low Pressure Turbine, low pressure turbine), MFP (Main Fuel Pump, main fuel pump), OTHS (Others, others);
  • HPC Blades High Pressure Compressor Blades
  • VSV Inner Shrouds Variable Stator Vane Inner Shrouds, adjustable stator blade inner cover
  • VSV Inner Shrouds include: Stg.2VSV Inner Shroud (Standard Adjustable Static Blade), Stg.3VSV Inner Shroud (Three-stage Adjustable Static Blade);
  • Stg.2VSV Inner Shroud The sub-parts included in the Stg.2VSV Inner Shroud are: Stg.2J-Hook (secondary J-hook), Stg.2 Anti-Rotation (secondary anti-rotation).
  • Step 2 Define a generic description template for the lesion.
  • Step 2.1 Define the damage that may occur on the part. Parts here refer to parts and sub parts.
  • the aircraft maintenance manual will clearly define the damage that may occur in each type of engine components and the data that needs to be collected after the damage occurs.
  • the parts hierarchy of the endoscopic inspection can be completed through the aircraft maintenance manual and other related literature. Construct.
  • the damage defines the data that may be acquired for each type of engine component damage and damage, and a generic description template for the damage of various engine components.
  • Step 2.2 defines the general description template.
  • the universal description template includes three parts: qualitative, positioning and quantitative. Among them: Qualitative refers to the definition of damage, positioning refers to the definition of the specific location of the damage, quantitative refers to the definition of the size of the damage; qualitative, positioning and quantitative to achieve a complete description of the damage.
  • Aeroengine is a highly complex and precise thermal machine.
  • the working environment and load of different units are different. Therefore, the damage and damage of different parts may not be collected in different parts. The same is true, and the damage requirements for different parts are different in the maintenance manual. Therefore, it is necessary to establish a general description template of the damage to describe the damage that may occur in each component hierarchy.
  • qualification refers to the definition of damage, that is, the specific type of damage.
  • this method uses crack as an example to use type 1 (Type 1), type 2 (Type 2), and type 3 (Type 3). Type is defined.
  • Type 1 (Type 1) is the main type.
  • the main type is crack. Since the same type of damage may have different subtypes on different parts of the engine, Type 1 cracks can be classified into Axial Crack, Radial Crack, and circumferential crack. Subtypes such as (Circumferential Crack).
  • Type 2 is a secondary type.
  • one type of damage may be caused by the continued deterioration of another type of damage; or one type of damage accompanied by another type of minor damage, the main type of type 2 (Type 2) auxiliary type This feature.
  • the auxiliary types are: Related to Tear, Related to Nick, etc.
  • Type 3 is a supplementary explanation.
  • the internal structure of the engine is complex, and in some cases, type 1 (primary type) and type 2 (auxiliary type) are not sufficient to fully define the type of damage, so additional explanations are needed; for example, for cracks, the supplementary explanations are: Connect to Combustion Holes, ExtendRadially to The Blade Tip, and the like.
  • Type 1, Type 2 and Type 3 mentioned in this step can be further extended to more levels as needed; the purpose of the multi-level definition mentioned in this step is to adopt a kind of The damage type is described in detail by the method of primary and secondary, sub-category, and machine.
  • Position determines the position of the component where the damage is located.
  • the geometry of the engine components is generally complex, so the position at which the damage is located needs to be determined.
  • Position 1 Position 1
  • Position 2 Position 2
  • Position Position (or referred to as First Position - Second Position - Orientation) is required for the components of the engine that are damaged except for the blade; When the blade is damaged, it is necessary to define the position of the component where the damage is located by using Airfoil-Position 1 - Position 2 - Location.
  • Airfoil Determine the position of the blade where the damage is located, such as the leading edge of the blade, the trailing edge of the blade, the Convex surface, and the concave surface.
  • Position 1 Determine the area of the component where the damage is located. Generally speaking, compared with the larger part, the area of the part is defined at the beginning of design, such as zone A and zone B.
  • Position 2 (second position): For some parts, only position 1 is not enough to accurately describe the area where the damage is located. It is necessary to define the description of the supplementary area. The specific definition needs to be based on the location of the part and the aircraft maintenance manual. The description is to determine.
  • Orientation Determine the location of the damage by specific numerical measurements.
  • the specific implementation method is as follows: firstly define the reference position of the measurement and/or the starting point of the measurement, then define the type of the value, and finally define the numerical unit; for example, the orientation of the crack on the blade can be expressed as:
  • the options for defining the position are: the distance of the crack from the leading edge of the blade, the type of input type is floating point, and the unit of distance is mm.
  • Quantification refers to the definition of the size of the damage. After the damage of the aero-engine, the damage size needs to be measured according to the maintenance manual provided by the manufacturer, and the corresponding maintenance measures are taken according to the damage size.
  • the dimension measurement is implemented by first defining the damage name of the desired measurement, then defining the type of the collected value, and finally defining the numerical unit; for example, defining the crack size on the blade can be expressed as:
  • the options for measuring size are: maximum crack length, the input type is floating point, and the length is in millimeters.
  • Step 2.3 specifies the qualitative, localized, and quantitative information required for a particular injury to a particular component.
  • the data to be collected for the damage and damage defined in steps 2.1 and 2.2 is defined for the possible occurrences of all parts of all engine models; in order to improve the efficiency of information entry and collection, the workload of the input personnel is reduced, and specific components are required. Damage is defined:
  • CFM56-7B engine HPC>HPC Blades>Stage 1HPC Blades>Crack High Pressure Compressor>High Pressure Compressor Blade>First Stage High Pressure Compressor Blade>Crack
  • the standard * field indicates that it is not allowed to be empty, that is, the input personnel must input the standard * information, and other fields can be filled in according to the actual situation.
  • a required field in step 2.3 For critical data in the endoscopic examination that affects the reliability of the engine components and has an important impact on the repeat inspection interval, it can be defined as a required field in step 2.3; in the standardized entry step, the required fields are * Number tag; if the required field is empty, submission is not allowed.
  • Step 3 Define an evaluation template for the component inspection results.
  • the evaluation template includes a record of the inspection result of the component. If the component inspection result finds damage, the evaluation template needs to record the following information:
  • the evaluation template only needs to be filled in the Remarks field for the input personnel to fill in the supplementary instructions.
  • the damage situation is complicated, and the corresponding conclusion cannot be given according to the manual standard.
  • the conclusion of the inspection result is to be determined, and it is necessary to further determine the inspection conclusion with the engine manufacturer.
  • Step 4 Define a unit damage summary template for endoscopic examination.
  • the Module is the largest layer in the component hierarchy of the engine endoscopic inspection.
  • the unit body summary template is implemented by first defining the damage type to be summarized, then defining the damage subclass, and finally defining the measurement size, ie,
  • step 2 using the damage generic template in step 2 to select the type of damage to be summarized; then, selecting the damage subclass from the qualitative part of step 2 according to the determined damage type;
  • the measured size is defined from the quantitative portion of step 2, based on the determined type of damage.
  • the damage summary template of the HPC unit of the CFM56-7B engine is:
  • Step 5 The endoscopic examination results are standardized and entered.
  • the standardized input of the data of the endoscopic examination specifically includes:
  • the standardizing the data of the endoscopic examination further includes: engine basic information; engine nameplate information.
  • Step 5.1 Collect basic information of the engine.
  • the basic information of the engine includes information such as aircraft installation, work basis, and endoscopic equipment. Workers need to enter basic engine information.
  • the details of the basic engine information are listed in the fields in the following table:
  • step 5.1 the basic engine information mentioned in step 5.1 is not limited to the fields mentioned in the above detailed information. In actual work, the worker can dynamically add other field information as needed.
  • Step 5.2 records the engine nameplate information.
  • the nameplate records the engine serial number, model thrust configuration and other information. By shooting the engine nameplate, the engine for this endoscopic inspection can be confirmed.
  • Step 5.3 records engine component damage information and evaluates the damage results, ie:
  • the engine component damage information is recorded according to the definition of the damage in step 2.1, and the damage result is evaluated according to the evaluation template in step 3.
  • Step 5.4 According to the definition of the unit damage summary template according to step 4, fill in the unit body summary information, that is,
  • Step 5.5 Repeat steps 5.3 and 5.4 until the records of all the parts for endoscopic inspection are completed;
  • the method provides an add, delete and fold/expand button after the entry of each piece of information; the folding/expanding button can be used to fold/expand the inspection result of the entire part.
  • composite damage In actual use, there may be cases where multiple damages occur at the same position of the component (ie, composite damage). This method defines the Combined Defect option. After the selection, the composite damage can be described. The damage is placed in the same part, and the specific implementation form is as follows:
  • Step 5.6 draw conclusions based on the endoscopic examination results
  • the inspection result of all the components in the unit is normal, and the inspection result of the automatic generation unit is normal;
  • the result of the inspection is that the component has been damaged, and the degree of damage is further deteriorated compared with the previous endoscopic examination.
  • the Accept with Reduced BSI Interval is required; the damage of the components is compared. Severe, the size of the damage has reached the standard of replacement (required for the renewal of the maintenance manual), and the acceptance with CIS Limit is required according to the time specified in the manual (flight cycle/hour); the damage of the components is serious and exceeds The range of damage allowed in the manual requires immediate replacement/rejection; and the damage caused by the components is complicated, and the corresponding conclusions cannot be given according to the manual standards.
  • the inspection results are to be determined, and the engine manufacturer is required to further determine the inspection results. (To Be Determined) components are automatically added to the conclusion;
  • the worker may check the result as indicating that there is damage on the part, the degree of damage is small, and the damage is not necessary. (Accept with No Further Action Required) and the damage indicating the part is not obvious compared with the result of the last endoscopy. Deterioration, the criteria for shortening the endoscopic examination required by the manual have not been met, and the components of the Accept with Continue BSI Interval, which was the same as the previous endoscopic examination, are added to the conclusion.
  • Step 6 Data verification.
  • Step 6.1 Compare engine basic information (including serial number, etc.), components and damage entered by the worker with historical data in the database;
  • Step 6.2 If the search finds that there is no record information of the engine under the damage of the component in the database, the check record of the article is directly stored in the database;
  • Step 6.3 Searching for the damage description of the engine in the location in the search database, the entry page will prompt the entry personnel to damage the result of the last endoscopic examination of the component, and the entry personnel can click to view the details of the last endoscopic examination. To better judge the damage;
  • Step 6.4 If the damage description of the engine in the database is found in the search, the record and the history record are verified, and the damage description that fails the verification cannot be submitted, and the previous measurement needs to be re-measured or modified. Peek into the inspection results; the verification formula is as follows:
  • d n refers to the damage data measured by this inspection
  • ⁇ refers to the error threshold allowed for damage measurement, generally ranging from -8% to -5%;
  • Step 6.5 Compare the repeated inspection interval recommended in the endoscopy inspection conclusion with the last inspection result. If the recommended repeated inspection interval entered in this inspection is greater than the repeated inspection interval input last time, the worker is reminded. It is recommended to verify the conclusion of this repeated inspection interval.
  • the method prohibits the same worker from performing two consecutive endoscopic examinations on the same part of the engine;
  • the worker After the worker inputs the engine serial number and selects the unit to be inspected, the result of the last endoscopic examination of the engine that meets the condition is automatically retrieved in the history database, and the worker is prompted to check the result of the last endoscopic examination to understand the station. Engine damage to prevent missing damage during this endoscopy.
  • Step 7 Data storage.
  • the data includes a photograph taken when an endoscope checks for damage to the device, the photo being stored in two forms, an original image (original photo) and a compressed image (compressed image).
  • the size of the original photo taken by the industrial endoscopic device is generally large. To improve the loading efficiency of the system, the size of the original photo needs to be compressed. When the preview or the reference mode is used, the compressed image is directly called. If the damage needs to be studied in detail, choose to call the original image for higher definition.
  • Step 8 Record presentation.
  • the present invention also discloses a system for recording data of endoscopic examination, wherein the endoscopic examination is to check whether a device is damaged by an endoscope, and the device is composed of components,
  • the system includes:
  • a component hierarchy module for constructing a component hierarchy of the device, the component hierarchy comprising two levels of a unit body and a component, the unit body comprising one or more components;
  • the universal description template includes three parts: qualitative, positioning and quantitative.
  • An evaluation module including an evaluation template, for recording the inspection result of the component. If the component inspection result finds damage, the evaluation template needs to record the following information: damage inspection result, suggestion and damage development trend;
  • a unit damage summary module for summarizing the unit body damage to define a unit body damage summary template, wherein the unit damage summary template includes: defining a main type and definition of the damage to be summarized. The subtype of damage and the size of the damage defined;
  • An endoscopic examination result standardized input module for standardizing data entered into the endoscopic examination, the data of the endoscopic examination includes:
  • a data verification module configured to verify the entered data, and compare the data of the endoscopic examination entered with the historical data in the database
  • a data storage module configured to store the entered data, the data includes a photo taken when an endoscope detects a damage to the device, and the photo is an original photo or a compressed photo;
  • a record presentation module for presenting the previously entered data when it is needed for review.
  • the analysis and implementation ideas of the method of the present invention are obviously not limited to the standardized entry problem of the endoscopic inspection result of the engine, and can also be adaptively adjusted for the target object of the endoscopic inspection: for the modular mechanical product, Layers are split into the innermost parts, and the damage of parts and unit body levels is defined, and the collected data is matched with relevant standards.
  • the method of the invention can be directly applied to the endoscope device operating system, and the report production can be directly completed at the same time as the endoscope inspection; or can be used as an independent data collection software to perform standardized input of the endoscope inspection result on the computer or tablet computer by the worker.
  • the standardized entry of endoscopic examination results provides a continuous and stable data source for the study of the development trend of endoscopic examination component damage, damage image recognition and endoscopic examination interval research. Based on the method, the overall development trend of internal damage can be quantified, which provides a good measure for improving the reliability of modular mechanical products.

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Abstract

一种将内窥检查的数据进行记录的方法和系统，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，包括：(1)构建所述设备的零部件层次结构；所述零部件层次结构包括单元体和部件两个层次，所述单元体包含一个或者多个部件；(2)定义所述损伤的通用描述模板；(3)定义所述部件检查结果的评估模板；(4)定义所述单元体损伤总结模板；(5)标准化录入所述内窥检查的数据；(6)根据所述内窥检查的数据得出结论，从而可通过对内部损伤的整体发展趋势进行量化，为提高模块化机械产品的可靠性提供了一种很好的度量方式。

Description

将内窥检查的数据进行记录的方法和系统 技术领域
本发明涉及数据处理领域，特别涉及一种将内窥检查的数据进行记录的方法和系统。
背景技术
航空发动机是一种高度复杂和精密的热力机械，为航空器提供飞行所需要的动力。现代航空发动机追求高功质比，高压气比，涡轮前温度越来越高；发动机尤其是核心机在高温、高压、高负载环境下工作，发动机部件的损伤及扩展情况直接影响到飞机的安全性和可靠性。
使用工业内窥镜查看发动机内部部件损伤是探明发动机内部实际损伤情况的最有效方法，通过工业内窥镜手段明确的飞机下发占到了总下发量60％以上。
根据适航当局要求，使用工业内窥镜对发动机做完内窥检查后，需要对检查结果进行记录，对发现的损伤及后续措施进行记录。目前，业内普遍采用Word或Excel对内窥检查进行撰写，以PDF文件形式进行保存。这种由工作者制作的内窥检查报告形式因人而异，主观性强，损伤描述及内窥重复检查间隔不尽详细，测量数据准确度不高，一般仅用作记录存档。该种存储方式无法通过计算机直接对检查结果展开研究，分析发动机损伤的变化趋势，导致飞机临时停场换发及非计划下发比例偏高，对航空公司运营和飞行安全带来隐患。
发明内容
本发明的目的在于提供一种将内窥检查的数据进行记录的方法和系统。
为了实现上述目的，本发明提供如下技术方案：
一种将内窥检查的数据进行记录的方法，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，包括：
(1)构建所述设备的零部件层次结构；
所述零部件层次结构包括单元体和部件两个层次，所述单元体包含一个或者多个部件；
(2)定义所述损伤的通用描述模板；
(3)定义所述部件检查结果的评估模板；
(4)定义所述单元体损伤总结模板；
(5)标准化录入所述内窥检查的数据；
(6)根据所述内窥检查的数据得出结论。
进一步地，在上述方法中，所述定义所述损伤的通用描述模板包括：对所述部件上可能会出现的所述损伤进行定义，和对所述通用描述模板进行定义。
进一步地，在上述方法中，所述通用描述模板包括定性、定位和定量三部分，所述定性是指对所述损伤进行定义，所述定位是指对损伤所在部件的位置进行确定，所述定量是指对损伤的尺寸进行定义。
进一步地，在上述方法中，所述定性是指以主类型、辅助类型和补充说明的方式对所述损伤进行定义，所述主类型包括不同的子类型。
进一步地，在上述方法中，所述定位是指以第一位置-第二位置-方位的方式对损伤所在部件的位置进行确定。
进一步地，在上述方法中，所述评估模板包括：损伤检查结果、建议和损伤发展趋势。
进一步地，在上述方法中，所述损伤检查结果包括：
A：所述部件出现了损伤，损伤程度很小，无需采取进一步措施；
B：所述部件出现的损伤与上一次内窥检查结果相比没有明显恶化，尚未达到缩短内窥检查的标准，采取和上一次内窥检查一样的重复检查标准；
C：所述部件出现了损伤，损伤程度与上一次内窥检查相比进一步恶化，需要缩短内窥重复检查间隔；
D：所述部件出现的损伤比较严重，损伤尺寸达到了更换标准，需要按照规定的时间完成更换；
E：所述部件出现的损伤严重，超出了允许的损伤尺寸范围，需要立即更换；
F：所述部件出现的损伤情况复杂，无法依据标准给出对应结论，检查结果待定，需要进一步与所述设备的制造商确定检查结果。
进一步地，在上述方法中，所述建议包括：下次重复检查的小时和/或循环数、期限下发的小时和/或循环数。
进一步地，在上述方法中，所述损伤发展趋势包括：新发现损伤、损伤未扩展和损伤扩展。
进一步地，在上述方法中，所述评估模板还包括：参考依据和补充说明。
进一步地，在上述方法中，所述定义所述单元体损伤总结模板包括：定义所需总结的损伤的主类型、定义损伤的子类型和定义损伤的尺寸。
进一步地，在上述方法中，所述标准化录入所述内窥检查的数据包括：
其中一个部件的下述信息：
1)向所述通用描述模板中录入信息；
2)向评估模板中录入信息；
3)向所述单元体损伤总结模板中录入信息；
其中另一个部件的下述信息：
重复1)、2)、3)；
直至将所有内窥检查的部件的记录完成。
进一步地，在上述方法中，当所述设备为航空发动机或者燃气轮机时，所述标准化录入所述内窥检查的数据进一步包括：
发动机基本信息；
发动机铭牌信息。
进一步地，在上述方法中，对所述单元体内所有部件检查结果均为正常的部件，自动生成所述单元体的检查结果为正常；
将所述损伤检查结果为C、D、E以及F的部件自动添加到结论中；
将所述损伤检查结果为A以及B的部件添加或者不添加到结论中。
进一步地，在上述方法中，进一步包括：数据校验，所述数据校验包括：
根据录入的所述发动机基本信息、部件和损伤与数据库中的历史数据进行对比；
若检索发现数据库中并不存在该台发动机在该部件损伤下的记录信息，则直接将本条检查记录存入数据库中；
检索发现数据库中已存在该台发动机在该部件的损伤描述，录入页面会提示录入人员该部件损伤上次内窥检查的结果，录入人员可点击查看上次内窥检查的详细情况，以更好对损伤进行判断；
若检索发现数据库中已存在该台发动机在该部件的损伤描述，则将本份记录和历史记录进行校验，校验不通过的损伤描述无法提交，需重新测量或修改上一次内窥检查结果；校验公式如下：
Figure PCTCN2017114583-appb-000001
其中：
d n指本次检查测量的损伤数据；
d p指上次检查测量的损伤数据；
δ指损伤测量允许的误差阈值，一般取值范围为-8％～-5％；
将本次内窥检查结论中建议的重复检查间隔与上次检查结果进行对比，若本次检查输入的建议重复检查间隔大于上次输入的重复检查间隔，则对工作者进行提醒，建议其对本次重复检查间隔结论进行校验。
进一步地，在上述方法中，进一步包括：数据存储，所述数据包括用内窥镜对设备是否出现损伤进行检查时拍摄的照片，所述照片为原始照片或者压缩后的图片。
进一步地，在上述方法中，进一步包括：记录展现，所述记录展现是指在查阅的时候能够将之前录入的所述数据展现。
本发明还公开一种将内窥检查的数据进行记录的系统，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，所述系统包括：
1)零部件层次结构模块，用于构建所述设备的零部件层次结构，所述零部件层次结构包括单元体和部件两个层次，所述单元体包含一个或者多个部件；
2)通用描述模块，用于对所述部件上可能会出现的所述损伤进行定义，和对所述通用描述模板进行定义；
所述通用描述模板包括定性、定位和定量三部分，所述定性是指对所述损伤进行定义，所述定位是指对损伤所在部件的位置进行确定，所述定量是 指对损伤的尺寸进行定义；
3)评估模块，包括评估模板，用于记录所述部件的检查结果，若部件检查结果发现损伤，则评估模板需记录如下信息：损伤检查结果、建议和损伤发展趋势；
4)单元体损伤总结模块，用于对所述单元体损伤进行总结，以定义单元体损伤总结模板，所述定义所述单元体损伤总结模板包括：定义所需总结的损伤的主类型、定义损伤的子类型和定义损伤的尺寸；
5)内窥检查结果标准化录入模块，用于标准化录入所述内窥检查的数据，所述内窥检查的数据包括：
其中一个部件的下述信息：
(1)向所述通用描述模板中录入信息，
(2)向所述评估模板中录入信息，
(3)向所述单元体损伤总结模板中录入信息，
其中另一个部件的下述信息：
重复(1)、(2)、(3)，
直至将所有内窥检查的部件的记录完成；
6)数据校验模块，用于对录入的数据进行校验，根据录入的所述内窥检查的数据与数据库中的历史数据进行对比；
7)数据存储模块，用于对录入的所述数据进行存储，所述数据包括用内窥镜对设备是否出现损伤进行检查时拍摄的照片，所述照片为原始照片或压缩后的照片；
8)记录展现模块，用于在需要查阅的时候将之前录入的所述数据展现。
分析可知，本发明公开的一种将内窥检查的数据进行记录的方法和系统，主要实现了如下技术效果：本发明所述方法可直接应用于内窥设备操作系统，在内窥检查的同时直接完成报告制作；亦可作为独立的数据采集软件由工作者在电脑或平板电脑完成内窥检查结果的标准化录入。内窥检查结果的标准化录入为研究内窥检查部件损伤的发展趋势研究、损伤图像识别及内窥检查间隔研究提供了持续稳定的数据源。在本方法基础上，可通过对内部损伤的整体发展趋势进行量化，为提高模块化机械产品的可靠性提供了一种很好的度量方式。
具体实施方式
下面将结合实施例来详细说明本发明。各个示例通过本发明的解释的方式提供而非限制本发明。实际上，本领域的技术人员将清楚，在不脱离本发明的范围或精神的情况下，可在本发明中进行修改和变型。例如，示为或描述为一个实施例的一部分的特征可用于另一个实施例，以产生又一个实施例。因此，所期望的是，本发明包含归入所附权利要求及其等同物的范围内的此类修改和变型。
根据本发明的实施例，提供了一种将内窥检查的数据进行记录的方法和系统，能够对航空发动机、燃气轮机的内部部件及部件损伤的图像、视频、文字进行标准化存储。
一种将内窥检查的数据进行记录的方法，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，该方法包括以下步骤：
步骤1：构建所述设备的零部件层次结构。
所述零部件层次结构可依次包括单元体和部件两个层次，所述单元体包含一个或者多个部件。进一步地，单元体(Module)可包括子单元体(Sub Module)，部件(Part)可包括子部件(Sub Part)，单元体，子单元体，部件，子部件共为四个层次，其包含关系为：单元体
Figure PCTCN2017114583-appb-000002
子单元体
Figure PCTCN2017114583-appb-000003
部件
Figure PCTCN2017114583-appb-000004
子部件。
一般而言，发动机由低压压气机、高压压气机、燃烧室、高压涡轮和低压涡轮五个单元体(Module)组成。不同类型发动机的具体设计构造不完全相同，因此需要一种通用的标准化方法对每一种类型的发动机建立层次结构。根据各飞机的维修手册(AMM)中对发动机内窥检查的文字说明构建发动机从单元体(Module)到子部件(Sub Part)的内窥检查的零部件层次结构。
[根据细则26改正28.05.2018]　
比如CFM56-7B发动机层次结构可大致表示为：如图1所示。
[根据细则26改正28.05.2018]　
其中：
单元体层(Module)中包含的内容有：LPC(Low Pressure Compressor、低压压气机)，HPC(High Pressure Compressor、高压压气机)，CC(Combustion Chamber、燃烧室)，HPT(High Pressure Turbine、高压涡轮)，HPTN(High Pressure Turbine Nozzle Guide Vine、高压涡轮导向叶片)，LPT(Low Pressure Turbine、低压涡轮)，MFP(Main Fuel Pump、主燃油泵)，OTHS(Others、其它)；
单元体HPC的子单元体层(Sub Module)中包含：HPC Blades(High Pressure Compressor Blades、高压压气机叶片)，VSV Inner Shrouds(Variable Stator Vane Inner Shrouds、可调静子叶片内罩)；
子单元体VSV Inner Shrouds包含的部件(Part)有：Stg.2VSV Inner Shroud(二级可调静子叶片)，Stg.3VSV Inner Shroud(三级可调静子叶片)；
部件Stg.2VSV Inner Shroud包含的子部件(Sub Part)有：Stg.2J-Hook(二级J形钩)，Stg.2Anti-Rotation(二级防转销)。
步骤2：定义所述损伤的通用描述模板。
步骤2.1：对部件上可能会出现的损伤进行定义。此处的部件指的是部件(Part)和子部件(Sub Part)。
损伤具体包含：没有损伤(Normal)、裂纹(Crack)、材料丢失(MissingMaterial)、撕裂(Tear)、缺口(Nick)、划痕(Scratch)、凹痕(Dent)、卷曲(Curl)、弯曲(Bend)等，详细损伤列表见附录一：航空发动机内窥检查常见损伤列表。
飞机维护手册会对每种类型的发动机各零部件可能会出现的损伤，及出现损伤后所需要采集的数据进行明确定义，可通过飞机维护手册等相关文献完成内窥检查的零部件层次结构的构建。
所述损伤对每一种类型的发动机各零部件可能会出现的损伤及损伤所需要采集的数据进行定义，构建发动机各零部件损伤的通用描述模板。
[根据细则26改正28.05.2018]　
比如CFM56-7B发动机HPC(单元体)>HPC Blades(子单元体)>Stage 1 HPC Blades(部件)上可能会出现的损伤情况如图4所示。
[根据细则26改正28.05.2018]　
步骤2.2对所述通用描述模板进行定义。
所述通用描述模板，包括定性、定位和定量三部分。其中：定性是指对损伤进行定义，定位是指对损伤的具体位置进行定义，定量是指对损伤的尺寸进行定义；通过定性、定位和定量实现对损伤的完整描述。
航空发动机是一种高度复杂和精密的热力机械，不同单元体的工作环境及所承受的负载不尽相同，因此不同零部件可能会出现的损伤及损伤在不同零部件所需要采集的数据也不尽相同，且维护手册中对在不同零部件出现的 损伤要求也不尽相同，因此需要建立损伤的通用描述模板对各个零部件层次结构中可能会出现的损伤进行描述。
通过通用描述模板实现所有损伤的定性、定位和定量信息的更新维护。
首先，说明一下定性的具体含义。定性(Type)是指对损伤进行定义，即给出损伤的具体类型。为保证对损伤类型的准确描述，需要将损伤类型进一步细化；本方法以裂纹(Crack)为例采用类型1(Type 1)、类型2(Type2)和类型3(Type 3)的方式对损伤类型进行定义。
类型1(Type 1)为主类型。主类型即裂纹(Crack)。由于同一种类型的损伤在发动机中的不同零部件上可能会出现不同的子类型，所以可将类型1的裂纹分为轴向裂纹(Axial Crack)、径向裂纹(Radial Crack)、周向裂纹(Circumferential Crack)等子类型。
类型2(Type 2)为辅助类型。某些情况下，一种类型损伤可能是由另外一种类型损伤持续恶化导致的；或一种类型损伤同时伴随了另外一种轻微损伤，类型2(Type 2)的辅助类型这一字段主要实现这一功能。比如对裂纹(Crack)而言，辅助类型有：与撕裂相关(Related to Tear)、与缺口相关(Related to Nick)等。
类型3为补充说明。发动机的内部构造复杂，某些情况下通过类型1(主类型)和类型2(辅助类型)不足以对损伤类型进行完整定义，因此需要进行补充说明；比如对裂纹而言，补充说明有：与燃烧孔相连(Connect to Combustion Holes)、径向延伸至叶尖(ExtendRadially to The Blade Tip)等。
需要说明的是，本步骤中提到的类型1、类型2和类型3的三级定义方式可根据需要进一步扩展至更多层级；本步骤中提到的多级定义的目的在于采用一种分主次、分类别、机器可直接识别利用的方法对损伤类型进行详细描述。
其次，说明一下定位的具体含义。定位(Position)即对损伤所在零部件的位置进行确定。发动机零部件的几何构型一般比较复杂，因此需要对损伤所在零的位置进行确定。发动机的部件中除了叶片以外的其他部件有损伤时需要采用位置1(Position 1)-位置2(Position 2)-方位(Location)(或者称为第一位置-第二位置-方位)进行定位；叶片有损伤时需要采用翼型(Airfoil)-位置1(Position 1)-位置2(Position 2)-方位(Location)的方式对损伤所 在部件的位置进行定义，其中：
翼型：对损伤所在叶片的位置进行确定，比如叶片前缘(Leading Edge)、叶片后缘(Trailing Edge)、凸面(Convex Surface)、凹面(Concave Surface)等。
位置1(第一位置)：对损伤所在部件的区域进行确定，一般而言，对比较大的部件，在设计之初会对部件的区域进行定义，比如A区、B区等。
位置2(第二位置)：对某些部件，仅靠位置1，不足以准确描述损伤所在区域，需要补充区域的描述定义，具体定义内容需根据部件所在位置及飞机维修手册对该部位损伤区域的描述来确定。
方位：通过具体的数值测量确定损伤所在位置。具体实现方法为：首先定义测量的参考位置和/或测量起点，然后定义数值类型，最后定义数值单位；比如在叶片上出现裂纹的方位可以表示为：
参考依据(Reference)：距离叶片前缘(From Leading Edge)
数字类型(Value Type)：浮点型(Float)
单位(Unit)：毫米(mm)
即如果在叶片上出现裂纹，可选择的位置定义选项是：裂纹距离叶片前缘的距离、输入的数字类型为浮点型、距离的单位是毫米。
再次，说明一下定量的具体含义。定量(Size)是指对损伤的尺寸进行定义，航空发动机出现损伤以后，需要依据厂家提供的维护手册对损伤尺寸进行测量，根据损伤尺寸采取对应的维护措施。尺寸测量的实现方法为：首先定义所需测量的损伤名称，然后定义采集数值类型，最后定义数值单位；比如对叶片上的裂纹尺寸进行定义可以表示为：
术语(Nomenclature)：最大裂纹长度(The Max Length)
数字类型(Value Type)：浮点型(Float)
单位(Unit)：毫米(mm)
即叶片上如果出现裂纹，可选择的测量尺寸选项是：最大裂纹长度、输入的数字类型是浮点型、长度的单位是毫米。
步骤2.3对特定部件出现的特定损伤所需要的定性、定位、定量信息进行规定。
步骤2.1和步骤2.2中所定义的损伤及损伤所需要采集的数据是针对所有发动机型号所有部位可能出现的情况定义的；为提高信息录入采集效率，减轻录入人员工作负担，需要针对特定部件的特定损伤进行定义：
比如CFM56-7B发动机HPC>HPC Blades>Stage 1HPC Blades>Crack(高压压气机>高压压气机叶片>第一级高压压气机叶片>裂纹)的损伤定义为：
Figure PCTCN2017114583-appb-000006
Figure PCTCN2017114583-appb-000007
其中标*字段表示不允许为空，即录入人员必须输入标*信息，其它字段录入人员可根据实际情况填写。
对内窥检查中涉及影响发动机部件可靠性及对内窥重复检查间隔有重要影响的损伤关键数据，可在步骤2.3中将其定义为必填字段；在标准化录入步骤中，必填字段以*号标记；若必填字段为空，则不允许提交。
需要说明的是，不同零部件的不同损伤所需的必填字段不尽相同，该方法正是通过本步骤对各零部件损伤所需要的必填字段进行定义。
步骤3：定义部件检查结果的评估模板。
所述评估模板中包括对部件检查结果的记录，若部件检查结果发现损伤，则评估模板需记录如下信息：
Figure PCTCN2017114583-appb-000008
若部件检查结果发现没有损伤(即检查结果为Normal)，这种情况下评估模板只需在Remarks字段中供录入人员填写补充说明即可。
其中损伤检查结果的字段说明包括：
Accept with No Further Action Required表示部件上出现了损伤，损伤程度很小，无需采取进一步措施；
Accept with Continue BSI Interval表示部件损伤与上一次内窥检查结果相比没有明显恶化，尚未达到手册要求的缩短内窥检查的标准，采取和上一次内窥检查一样的重复检查标准；
Accept with Reduced BSI Interval表示部件出现了损伤，损伤程度与上一次内窥检查相比有进一步恶化，根据维修手册要求需要缩短内窥重复检查间隔；
Accept with CIS Limit损伤比较严重，损伤尺寸达到了维护手册要求的期限换发标准，需要按照手册规定的飞行循环/小时内完成换发工作；
Reject损伤严重，超出了手册允许的损伤尺寸范围，需要立即换发；
To be Determined损伤情况复杂，无法依据手册标准给出对应结论，检查结果结论待定，需要进一步与发动机制造商确定检查结论。
步骤4：定义内窥检查的单元体损伤总结模板。
单元体(Module)为发动机内窥检查的零部件层次结构中的最大层。
根据某些机型的飞机维护手册要求，当单元体中的某些部件出现损伤时，需要对整个单元体的损伤进行汇总，因此需要建立单元体损伤总结模板。
单元体总结模板的实现方法为：首先定义所需总结的损伤类型，然后定义损伤子类，最后定义测量尺寸，即，
首先，利用步骤2中的损伤通用模板选择所需总结的损伤类型；然后，根据已确定的损伤类型，从步骤2的定性部分选择损伤子类；
最后，根据已确定的损伤类型，从步骤2的定量部分定义测量尺寸。
比如CFM56-7B发动机HPC单元体的损伤总结模板为：
类型：裂纹
(Type:Crack)
主类型：叶尖径向裂纹,自叶尖开始的弦向裂纹
(Primary Type:Radial Tip Crack,Chord-Wise Crack From The Tip)
尺寸：5到9级高压压气机损伤叶片数，单位：整数型，单位：个
(Size:Nomenclature:Stg.5Thru 9Damaged Blades,Type:Int,Unit:ea)
步骤5：内窥检查结果标准化录入。
所述标准化录入所述内窥检查的数据，具体包括：
其中一个部件的下述信息：
1)向所述通用描述模板中录入信息；
2)向评估模板中录入信息；
3)向所述单元体损伤总结模板中录入信息；
其中另一个部件的下述信息：
重复1)、2)、3)；
直至将所有内窥检查的部件的记录完成。
当所述设备为航空发动机或者燃气轮机时，所述标准化录入所述内窥检查的数据，进一步包括：发动机基本信息；发动机铭牌信息。
发动机部件损伤信息并对损伤结果进行评估、根据步骤4中的对单元体损伤总结模板的定义，填写单元体总结信息；内窥检查结果结论。
内窥检查结果标准化录入按以下步骤具体操作：
步骤5.1：采集发动机基本信息，发动机基本信息包括飞机装机、工作依据、内窥设备等信息，工作者需录入发动机基本信息。发动机基本信息的详细信息列举如下表中的字段所示：
字段 说明
Fleet 明确内窥检查发动机所属航空公司及执管单位
Borescope 记录内窥检查设备信息
ESN 发动机序列号
A/C Reg.Pos 发动机所在飞机位置
Base 执管单位
Engine Configuration 发动机构型
TSN/CSN 发动机自新小时/循环数
TSR/CSR 发动机自返修后小时/循环数
BSI Date 内窥检查日期
Task Card/NRC/EO 内窥检查工作所依据的工卡/非例行工卡/EO号
Reason 内窥检查工作原因
Content 内窥检查所涉及到的单元体或特殊部位
需要说明的是，步骤5.1中所提到的发动机基本信息并不仅限于上述详细信息里提到的字段，实际工作中，工作者可根据需要动态添加其它字段信息。
步骤5.2记录发动机铭牌信息，铭牌记录了发动机序列号、机型推力构型等信息，通过拍摄发动机铭牌，可以确认本次内窥检查的发动机。
步骤5.3记录发动机部件损伤信息并对损伤结果进行评估，即：
1)向所述通用描述模板中录入信息，以及
2)向评估模板中录入信息：
其中，根据步骤2.1中对损伤的定义记录发动机部件损伤信息，并根据步骤3中的评估模板对损伤结果进行评估。
[根据细则26改正28.05.2018]　
若部件检查结果发现没有损伤，则只需要在检查结果中选择Normal并上传对应位置的内窥检查照片即可；比如CFM56‐7B发动机第4级高压压气机叶片检查结果正常，其大致描述方式如图2所示。
[根据细则26改正28.05.2018]　
[根据细则26改正28.05.2018]　
[根据细则26改正28.05.2018]　
若检查发现损伤，则需要根据步骤2和步骤3中的内容对损伤进行描述并上传对应位置的内窥检查照片；比如CFM56‐7B发动机第8级高压压气机叶片检查发现缺口，其描述方式如图3所示。
[根据细则26改正28.05.2018]　
[根据细则26改正28.05.2018]　
步骤5.4根据步骤4对单元体损伤总结模板的定义，填写单元体总结信息，即
3)向所述单元体损伤总结模板中录入信息；
步骤5.5：重复步骤5.3、步骤5.4，直至将所有内窥检查的部件的记录完成；
需要说明的是：考虑到录入方式的便捷性，本方法在每条信息的录入后面提供了添加、删除和折叠/展开按钮；通过折叠/展开按钮可将整个部件的检查结果进行折叠/展开。
在实际使用过程中，可能会发生部件同一位置有多种损伤同时出现的情 况(即复合损伤)，本方法定义了复合损伤(Combined Defect)选项，选中后可对复合损伤进行描述，将多个损伤置于同一部位，具体实现形式如下图所示：
Figure PCTCN2017114583-appb-000013
Figure PCTCN2017114583-appb-000014
步骤5.6：根据内窥检查结果得出结论；
结论主要包括以下几种：
对单元体内所有部件检查结果均为正常的部件，自动生成单元体的检查结果正常；
将检查结果为表示部件出现了损伤，损伤程度与上一次内窥检查相比有进一步恶化，根据维修手册要求需要缩短内窥重复检查间隔(Accept with Reduced BSI Interval)；所述部件出现的损伤比较严重，损伤尺寸达到了更换(维护手册要求的期限换发)标准，需要按照手册规定的时间(飞行循环/小时)完成换发工作(Accept with CIS Limit)；所述部件出现的损伤严重，超出了手册允许的损伤尺寸范围，需要立即更换/换发(Reject)；和所述部件出现的损伤情况复杂，无法依据手册标准给出对应结论，检查结果待定，需要进一步与发动机制造商确定检查结果(To Be Determined)的部件自动添加到结论中；
工作人员可视情况将检查结果为表示部件上出现了损伤，损伤程度很小，无需采取进一步措施(Accept with No Further Action Required)和表示部件出现的损伤与上一次内窥检查结果相比没有明显恶化，尚未达到手册要求的缩短内窥检查的标准，采取和上一次内窥检查一样的重复检查标准(Accept with Continue BSI Interval)的部件添加到结论中。
比如某次CFM56‐7B发动机的内窥检查结果为：
燃烧室结论：正常
(CC Result:Normal)
高压涡轮静子导向叶片结论：记录1：HPTN凹面>烧蚀、裂纹
接受且无需采取进一步措施
记录2：根部外侧>烧穿
接受且采取400循环重复内窥检查
记录3：HPTN凸面>裂纹
接受且采取800循环重复检查
(HPTNGV Result:Record 1CONVAVE SURFACES OF HPTN>BURN,CRACK
Accept with No Further Action Required
Record 2 OUTER PLATFORM>BURN THROUGH
Accept with Continue BSI Interval 400Cycles,Hours
Record 3CONVEXSURPACES OF HPTN>CRACK
Accept with Continue BSI Interval 800Cycles,Hours)
高压涡轮结论：记录1：HPT前缘>材料丢失
接受且无需采取进一步措施
(HPT Result:Record 1LEADING EDGES OF HPT>MISSING MATERIAL
Accept with No Further Action Required)
补充说明：
(Remarks:)
步骤6：数据校验。
根据损伤发展的一般规律，在发动机拆下进行翻修之前，损伤自出现开始是持续恶化或保持不变的过程；因此，本方法会对工作者的录入数据进行校验，其具体实现过程如下：
步骤6.1：根据工作者录入的发动机基本信息(包括序列号等)、部件和损伤与数据库中的历史数据进行对比；
步骤6.2：若检索发现数据库中并不存在该台发动机在该部件损伤下的记录信息，则直接将本条检查记录存入数据库中；
步骤6.3：检索发现数据库中已存在该台发动机在该部位的损伤描述，录入页面会提示录入人员该部件损伤上次内窥检查的结果，录入人员可点击查 看上次内窥检查的详细情况，以更好对损伤进行判断；
步骤6.4：若检索发现数据库中已存在该台发动机在该部件的损伤描述，则将本份记录和历史记录进行校验，校验不通过的损伤描述无法提交，需重新测量或修改上一次内窥检查结果；校验公式如下：
Figure PCTCN2017114583-appb-000015
其中：d n指本次检查测量的损伤数据；
d p指上次检查测量的损伤数据；
δ指损伤测量允许的误差阈值，一般取值范围为-8％～-5％；
步骤6.5：将本次内窥检查结论中建议的重复检查间隔与上次检查结果进行对比，若本次检查输入的建议重复检查间隔大于上次输入的重复检查间隔，则对工作者进行提醒，建议其对本次重复检查间隔结论进行校验。
另外，鉴于发动机内窥检查的重要性，为防止人为差错，本方法程序上禁止同一工作者对发动机同一部位进行连续两次内窥检查；
在工作者输入发动机序列号并选定所检查单元体后，在历史数据库中自动检索符合条件的该台发动机上次内窥检查结果，并提示工作者查看上次内窥检查结果，了解该台发动机损伤情况，防止在本次内窥检查中遗漏损伤。
步骤7：数据存储。
所述数据包括用内窥镜对设备是否出现损伤进行检查时拍摄的照片进行存储，所述照片以两种形式存储，分别是原图(原始照片)和压缩图(压缩后的图片)形式。
工业内窥设备拍摄的原始照片尺寸一般比较大，为提高系统加载效率，需要对原始照片的尺寸进行压缩；在预览或者查阅模式时直接调用压缩后图片，若需要对损伤进行详细研究，则可选择调用原图以获取更高清晰度。
步骤8：记录展现。
查阅记录的时候能够将之前录入的所有数据记录展现。
与上述方法对应，本发明还公开了一种将内窥检查的数据进行记录的系 统，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，该系统包括：
1)零部件层次结构模块，用于构建所述设备的零部件层次结构，所述零部件层次结构包括单元体和部件两个层次，所述单元体包含一个或者多个部件；
2)通用描述模块，用于对所述部件上可能会出现的所述损伤进行定义，和对所述通用描述模板进行定义；
所述通用描述模板包括定性、定位和定量三部分，所述定性是指对所述损伤进行定义，所述定位是指对损伤所在部件的位置进行确定，所述定量是指对损伤的尺寸进行定义；
3)评估模块，包括评估模板，用于记录所述部件的检查结果，若部件检查结果发现损伤，则评估模板需记录如下信息：损伤检查结果、建议和损伤发展趋势；
4)单元体损伤总结模块，用于对所述单元体损伤进行总结，以定义单元体损伤总结模板，所述定义所述单元体损伤总结模板包括：定义所需总结的损伤的主类型、定义损伤的子类型和定义损伤的尺寸；
5)内窥检查结果标准化录入模块，用于标准化录入所述内窥检查的数据，所述内窥检查的数据包括：
其中一个部件的下述信息：
(1)向所述通用描述模板中录入信息，
(2)向所述评估模板中录入信息，
(3)向所述单元体损伤总结模板中录入信息，
其中另一个部件的下述信息：
重复(1)、(2)、(3)，
直至将所有内窥检查的部件的记录完成；
6)数据校验模块，用于对录入的数据进行校验，根据录入的所述内窥检查的数据与数据库中的历史数据进行对比；
7)数据存储模块，用于对录入的所述数据进行存储，所述数据包括用内窥镜对设备是否出现损伤进行检查时拍摄的照片，所述照片为原始照片或压缩后的照片；
8)记录展现模块，用于在需要查阅的时候将之前录入的所述数据展现。
本发明所述方法的分析和实现思路，显然并不局限于发动机内窥检查结果的标准化录入问题，还可针对内窥检查的目标对象，进行适应性的调整：对模块化机械产品，将其层层拆分至最内层部件，对部件及单元体级的损伤进行定义，对采集到的数据与相关标准进行匹配。
本发明所述方法可直接应用于内窥设备操作系统，在内窥检查的同时直接完成报告制作；亦可作为独立的数据采集软件由工作者在电脑或平板电脑完成内窥检查结果的标准化录入。内窥检查结果的标准化录入为研究内窥检查部件损伤的发展趋势研究、损伤图像识别及内窥检查间隔研究提供了持续稳定的数据源。在本方法基础上，可通过对内部损伤的整体发展趋势进行量化，为提高模块化机械产品的可靠性提供了一种很好的度量方式。
以上所述仅为本发明的优选实施例，并不用于限制本发明，对于本领域的技术人员来说，本发明可以有各种更改和变化。凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。
[根据细则26改正28.05.2018]　
[根据细则26改正28.05.2018]　
[根据细则26改正28.05.2018]　
[根据细则26改正28.05.2018]　

Claims (18)

  1. 一种将内窥检查的数据进行记录的方法，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，其特征在于，包括：
    (1)构建所述设备的零部件层次结构；
    所述零部件层次结构包括单元体和部件两个层次，所述单元体包含一个或者多个部件；
    (2)定义所述损伤的通用描述模板；
    (3)定义所述部件检查结果的评估模板；
    (4)定义所述单元体损伤总结模板；
    (5)标准化录入所述内窥检查的数据；
    (6)根据所述内窥检查的数据得出结论。
  2. 根据权利要求1所述的方法，其特征在于，所述定义所述损伤的通用描述模板包括：
    对所述部件上可能会出现的所述损伤进行定义，和
    对所述通用描述模板进行定义。
  3. 根据权利要求2所述的方法，其特征在于，所述通用描述模板包括定性、定位和定量三部分，所述定性是指对所述损伤进行定义，所述定位是指对损伤所在部件的位置进行确定，所述定量是指对损伤的尺寸进行定义。
  4. 根据权利要求3所述的方法，其特征在于，所述定性是指以主类型、辅助类型和补充说明的方式对所述损伤进行定义，所述主类型包括不同的子类型。
  5. 根据权利要求3所述的方法，其特征在于，所述定位是指以第一位置-第二位置-方位的方式对损伤所在部件的位置进行确定。
  6. 根据权利要求1所述的方法，其特征在于，所述评估模板包括：损伤检查结果、建议和损伤发展趋势。
  7. 根据权利要求6所述的方法，其特征在于，所述损伤检查结果包括：
    A：所述部件出现了损伤，损伤程度很小，无需采取进一步措施；
    B：所述部件出现的损伤与上一次内窥检查结果相比没有明显恶化，尚未达到缩短内窥检查的标准，采取和上一次内窥检查一样的重复检查标准；
    C：所述部件出现了损伤，损伤程度与上一次内窥检查相比进一步恶化，需要缩短内窥重复检查间隔；
    D：所述部件出现的损伤比较严重，损伤尺寸达到了更换标准，需要按照规定的时间完成更换；
    E：所述部件出现的损伤严重，超出了允许的损伤尺寸范围，需要立即更换；
    F：所述部件出现的损伤情况复杂，无法依据标准给出对应结论，检查结果待定，需要进一步与所述设备的制造商确定检查结果。
  8. 根据权利要求6所述的方法，其特征在于，所述建议包括：下次重复检查的小时和/或循环数、期限下发的小时和/或循环数。
  9. 根据权利要求6所述的方法，其特征在于，所述损伤发展趋势包括：新发现损伤、损伤未扩展和损伤扩展。
  10. 根据权利要求6所述的方法，其特征在于，所述评估模板还包括：参考依据和补充说明。
  11. 根据权利要求4所述的方法，其特征在于，所述定义所述单元体损伤总结模板包括：定义所需总结的损伤的主类型、定义损伤的子类型和定义损伤的尺寸。
  12. 根据权利要求1所述的方法，其特征在于，所述标准化录入所述内 窥检查的数据包括：
    其中一个部件的下述信息：
    1)向所述通用描述模板中录入信息；
    2)向评估模板中录入信息；
    3)向所述单元体损伤总结模板中录入信息；
    其中另一个部件的下述信息：
    重复1)、2)、3)；
    直至将所有内窥检查的部件的记录完成。
  13. 根据权利要求12所述的方法，其特征在于，当所述设备为航空发动机或者燃气轮机时，所述标准化录入所述内窥检查的数据进一步包括：
    发动机基本信息；
    发动机铭牌信息。
  14. 根据权利要求7所述的方法，其特征在于，
    对所述单元体内所有部件检查结果均为正常的部件，自动生成所述单元体的检查结果为正常；
    将所述损伤检查结果为C、D、E以及F的部件自动添加到结论中；
    将所述损伤检查结果为A以及B的部件添加或者不添加到结论中。
  15. 根据权利要求13所述的方法，其特征在于，进一步包括：数据校验，所述数据校验包括：
    根据录入的所述发动机基本信息、部件和损伤与数据库中的历史数据进行对比；
    若检索发现数据库中并不存在该台发动机在该部件损伤下的记录信息，则直接将本条检查记录存入数据库中；
    检索发现数据库中已存在该台发动机在该部件的损伤描述，录入页面会提示录入人员该部件损伤上次内窥检查的结果，录入人员可点击查看上次内窥检查的详细情况，以更好对损伤进行判断；
    若检索发现数据库中已存在该台发动机在该部件的损伤描述，则将本份 记录和历史记录进行校验，校验不通过的损伤描述无法提交，需重新测量或修改上一次内窥检查结果；校验公式如下：
    Figure PCTCN2017114583-appb-100001
    其中：
    d n指本次检查测量的损伤数据；
    d p指上次检查测量的损伤数据；
    δ指损伤测量允许的误差阈值，一般取值范围为-8％～-5％；
    将本次内窥检查结论中建议的重复检查间隔与上次检查结果进行对比，若本次检查输入的建议重复检查间隔大于上次输入的重复检查间隔，则对工作者进行提醒，建议其对本次重复检查间隔结论进行校验。
  16. 根据权利要求1所述的方法，其特征在于，进一步包括：数据存储，所述数据包括用内窥镜对设备是否出现损伤进行检查时拍摄的照片，所述照片为原始照片或者压缩后的图片。
  17. 根据权利要求1所述的方法，其特征在于，进一步包括：记录展现，所述记录展现是指在查阅的时候能够将之前录入的所述数据展现。
  18. 一种将内窥检查的数据进行记录的系统，所述内窥检查是用内窥镜对设备是否出现损伤进行检查，所述设备由零部件组成，其特征在于，所述系统包括：
    1)零部件层次结构模块，用于构建所述设备的零部件层次结构，所述零部件层次结构包括单元体和部件两个层次，所述单元体包含一个或者多个部件；
    2)通用描述模块，用于对所述部件上可能会出现的所述损伤进行定义，和对所述通用描述模板进行定义；
    所述通用描述模板包括定性、定位和定量三部分，所述定性是指对所述损伤进行定义，所述定位是指对损伤所在部件的位置进行确定，所述定量是指对损伤的尺寸进行定义；
    3)评估模块，包括评估模板，用于记录所述部件的检查结果，若部件检查结果发现损伤，则评估模板需记录如下信息：损伤检查结果、建议和损伤发展趋势；
    4)单元体损伤总结模块，用于对所述单元体损伤进行总结，以定义单元体损伤总结模板，所述定义所述单元体损伤总结模板包括：定义所需总结的损伤的主类型、定义损伤的子类型和定义损伤的尺寸；
    5)内窥检查结果标准化录入模块，用于标准化录入所述内窥检查的数据，所述内窥检查的数据包括：
    其中一个部件的下述信息：
    (1)向所述通用描述模板中录入信息，
    (2)向所述评估模板中录入信息，
    (3)向所述单元体损伤总结模板中录入信息，
    其中另一个部件的下述信息：
    重复(1)、(2)、(3)，
    直至将所有内窥检查的部件的记录完成；
    6)数据校验模块，用于对录入的数据进行校验，根据录入的所述内窥检查的数据与数据库中的历史数据进行对比；
    7)数据存储模块，用于对录入的所述数据进行存储，所述数据包括用内窥镜对设备是否出现损伤进行检查时拍摄的照片，所述照片为原始照片或压缩后的照片；
    8)记录展现模块，用于在需要查阅的时候将之前录入的所述数据展现。
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DE102018209609A1 (de) * 2018-06-14 2019-12-19 MTU Aero Engines AG Inspektionsverfahren und System
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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020123915A1 (en) * 2001-03-01 2002-09-05 Denning Paul Dean Methods and systems for aviation nonconformance component management
CN101178385A (zh) * 2007-12-05 2008-05-14 南京航空航天大学 基于应变片的电涡流无损检测系统
CN102288412A (zh) * 2011-05-04 2011-12-21 哈尔滨工业大学 基于损伤基线的航空发动机硬件损伤分析与寿命预测方法

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8310533B2 (en) * 2006-03-27 2012-11-13 GE Sensing & Inspection Technologies, LP Inspection apparatus for inspecting articles
US8587660B2 (en) * 2010-07-30 2013-11-19 General Electric Company Image recording assemblies and coupling mechanisms for stator vane inspection
US8606597B2 (en) * 2011-02-24 2013-12-10 Olympus Corporation Endoscope inspection report creating apparatus, creating method of endoscope inspection report and storage medium
GB201109858D0 (en) * 2011-06-13 2011-07-27 Lewis Terry Method and system for aircraft inspections
DE102011114541A1 (de) * 2011-09-30 2013-04-04 Lufthansa Technik Ag Endoskopiesystem und korrespondierendesVerfahren zur Untersuchung von Gasturbinen
CN103514343B (zh) * 2012-06-18 2018-03-09 奥林巴斯株式会社 内窥镜检查报告生成装置和内窥镜检查报告生成方法
JP6000679B2 (ja) * 2012-06-20 2016-10-05 オリンパス株式会社 内視鏡装置、内視鏡画像記録用フォルダ生成方法及びプログラム
US20140139658A1 (en) * 2012-11-20 2014-05-22 General Electric Company Remote visual inspection system and method
US9446860B2 (en) * 2013-10-04 2016-09-20 Airbus Operations (Sas) Aircraft part and subassembly damage reporting method, system and mobile computer software application
US20150350553A1 (en) * 2014-05-31 2015-12-03 General Electric Company Systems and methods for menu directed inspection
CN104200319B (zh) * 2014-08-28 2018-05-11 北京中盈安信技术服务股份有限公司 基于管道完整性管理技术的油气管道施工数据监督方法
FR3033046B1 (fr) * 2015-02-23 2019-06-14 Safran Aircraft Engines Procede et dispositif de controle de l'etat d'un moteur d'aeronef a distance
JP6641172B2 (ja) * 2015-12-14 2020-02-05 オリンパス株式会社 内視鏡業務支援システム
CN106556605B (zh) * 2016-11-25 2018-05-15 交通运输部公路科学研究所 桥梁现场检测典型病害的数字化表征系统

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020123915A1 (en) * 2001-03-01 2002-09-05 Denning Paul Dean Methods and systems for aviation nonconformance component management
CN101178385A (zh) * 2007-12-05 2008-05-14 南京航空航天大学 基于应变片的电涡流无损检测系统
CN102288412A (zh) * 2011-05-04 2011-12-21 哈尔滨工业大学 基于损伤基线的航空发动机硬件损伤分析与寿命预测方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
XU, WENJUN, RESEARCH ON DEFECTS-EVALUATING SYSTEM FOR AEROENGINE BORESCOPIC INSPECTION, 3 September 2007 (2007-09-03), pages 7 *

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