FIELD: machine building.
SUBSTANCE: lining of aircraft engine comprises several hardened layers of prepreg with different orientation of fibers consisting of several segments with width that corresponds to skin length. Segments are located in the direction of skin perimeter with overlapping. In combination with layers of prepreg there is at least one reinforcing layer of prepreg arranged in several turns. Prepreg strip fibers are arranged in direction of length of prepreg strip. Strip of prepreg of every reinforcing layer is arranged with lateral overlapping. When making aircraft engine lining several layers of prepreg with different fiber orientation are arranged on mold and cured. Prior to hardening, in addition to prepreg layers, at least one reinforcing layer is placed on the mold from prepreg strip located in several turns.
EFFECT: group of inventions increases strength of aircraft engine skin.
16 cl, 12 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SKIN ELEMENT AS AIRCRAFT FUSELAGE PART | 2008 |
|
RU2466905C2 |
| COMPOSITE LIGHT-WEIGHT VANE, PRIMARILY FOR AIRCRAFT ENGINE FANS | 2008 |
|
RU2384750C1 |
| CARBON COMPOSITE THREADED CONNECTING ELEMENT BASED ON 3D SOLID-WOVEN PREFORM | 2023 |
|
RU2801427C1 |
| METHOD OF PRODUCTION OF COMPOSITE MATERIAL ON BASE OF INTER-METALLIC TITANIUM COMPOUND AND ARTICLE PRODUCED BY THIS METHOD | 2001 |
|
RU2215816C2 |
| OPTIMIZED CROSS-ORIENTATION OF LAYERS IN COMPOSITE LAMINATES | 2013 |
|
RU2644203C2 |
| LOCOMOTIVE GEARING CASING MANUFACTURING METHOD | 2023 |
|
RU2825006C1 |
| PART FROM COMPOSITE MATERIAL | 2016 |
|
RU2740763C2 |
| GLASS PLASTIC AND ARTICLE MADE THEREOF | 2014 |
|
RU2560419C1 |
| BAND PREPREG FOR FABRICATION OF THERMAL-PROTECTIVE COATING OF PRESSURE RESTRAINT LAYER OF HYPERSONIC RE-ENTRY AIRCRAFT HOUSING | 2014 |
|
RU2568515C1 |
| COMPOSITE ARTICLE MANUFACTURING METHOD | 2015 |
|
RU2697451C2 |
