FIELD: engines and pumps.
SUBSTANCE: turbomachine composite material blade comprises vane made up of alternating and oriented layers of composite material interjointed by a binder material and V-shape cross section metal strips arranged on the blade vane rear and front edges. The part of inner space of the front edge metal strip adjoining point of its profile bend incorporates composite material arranged in layers across the blade vane furnished with reinforcing fibres located between adjacent layers and directed along the blade vane profile centerline.
EFFECT: higher impact strength of front and rear edges, uniform distribution of deformation resulted from every impact on edges, which allows using smaller-thickness edges.
7 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOMACHINE COMPOSITION BLADE | 2005 |
|
RU2282726C1 |
| GAS-TURBINE ENGINE CONTAINING FAN AND COMPRESSOR | 2016 |
|
RU2625078C1 |
| WORKING WHEEL OF THE FAN AND COMPRESSOR AND METHOD OF ITS MANUFACTURE FROM COMPOSITE MATERIAL | 2015 |
|
RU2617752C2 |
| TURBOMACHINE COMPOSITE BLADE | 1984 |
|
RU1313055C |
| AVIATION ENGINE IMPELLER AND METHOD FOR MANUFACTURE THEREOF FROM COMPOSITE MATERIAL | 2017 |
|
RU2679956C1 |
| CENTRIFUGAL COMPRESSOR IMPELLER FROM COMPOSITE MATERIAL AND METHOD OF MAKING THEREOF | 2015 |
|
RU2600213C1 |
| CENTRIFUGAL COMPRESSOR IMPELLER FROM COMPOSITE MATERIAL | 2016 |
|
RU2651903C1 |
| FAN BLADE OF GAS TURBINE ENGINE | 2017 |
|
RU2667220C1 |
| GAS TURBINE ENGINE FAN BLADE | 2017 |
|
RU2675161C1 |
| FAN IMPELLER WITH FAIRING AND COMPOSITE MANUFACTURING METHOD | 2018 |
|
RU2689498C1 |
