Borescope Guide Pipe for Jet Engine Blade Serial Number Identification
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Solution Overview
Problem
Current methods for inspecting turbine blades in jet engines, particularly high-pressure turbine blades, fail to allow for clear identification of serial numbers in fully assembled engines, requiring costly and complex disassembly to document damage or changes, and lack precise association of serial numbers with individual blades during borescope inspections.
Innovation Solution
A device featuring a bend-free guide pipe with a securing mechanism for precise positioning and orientation of a flexible borescope, allowing clear and reproducible identification of turbine blades by directing the borescope between guide blades and using a securing device with an orientation unit to adjust the guide pipe's orientation relative to the jet engine, enabling clear association of serial numbers with individual blades.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If turbine blades are inserted into the engine with serial numbers on the base, then the engine structure is complete and functional, but the serial numbers become invisible and cannot be directly examined
Solution Approach 1:
A borescope is introduced as an intermediary inspection tool that can visually access the serial numbers on turbine blade bases through the engine structure without requiring disassembly. The borescope transmits images from the hidden serial number location to the exterior where they can be read and documented.
Solution Approach 2:
The patent establishes a systematic methodology for preliminary positioning and orientation of the borescope before inspection begins. By pre-defining the correct angular position and insertion depth, the inspection process can directly capture serial numbers without trial-and-error adjustments during actual use.
2Ease of operation
If a flexible borescope is used to inspect high-pressure turbine blades through a through-opening, then the borescope can reach the turbine blades, but precise positioning and orientation cannot be achieved
Solution Approach 1:
The patent replaces manual, trial-and-error mechanical positioning with a systematic orientation method based on angular measurements and reference markings. By defining specific angular positions relative to engine components, the borescope can be precisely positioned without requiring complex mechanical adjustment mechanisms.
Solution Approach 2:
The orientation method described in the patent is designed to be universally applicable to different engine types and turbine blade configurations. By using standardized reference points and angular measurements, the same basic procedure can be adapted to various engine designs without requiring custom positioning mechanisms for each application.
3Productivity
If general examination of all turbine blades is performed without individual identification, then inspection coverage is achieved, but clear association of serial numbers with individual blades is not possible
Solution Approach 1:
The patent implements a feedback mechanism where the inspectsor can verify the position of the borescope by observing reference markings or features visible in the field of view. This feedback allows the inspectsor to confirm they are viewing the correct blade with the correct serial number, enabling accurate documentation and tracking of individual blade conditions.
Solution Approach 2:
The borescope creates visual copies (images) of the serial numbers and blade conditions that can be documented and stored. These optical copies serve as permanent records that can be associated with specific blade serial numbers, enabling traceability and historical tracking of individual blade performance and degradation without requiring physical tags or labels on the blades themselves.
Data Source
AI summary
A device enables borescope inspection of turbine blades of a high-pressure turbine stage of a jet engine. The device has a bend-free guide pipe for introducing a flexible borescope. The device also has: a guide for the guide pipe, the guide being configured to provide clear and reproducible positioning and orientation of the guide pipe; and a securing device configured to releasably secure the guide to an outer side of the jet engine. The securing device is configured to adjust the guide to a predetermined orientation with respect to the outer side of the jet engine. The guide pipe is rigid and shaped in such a manner that an end of the guide pipe that is introduced into the jet engine when the guide is orientated correctly is orientable so as to be directed between two predetermined guide blades.