FIELD: engines and pumps.
SUBSTANCE: turbojet engine crankcase sheathing comprises two coaxial shells arranged one inside the other and rigidly jointed together by radial jackets that accommodate crankcase radial ducts. Sheathing inner shell lower edge is secured on crankcase element and rests axially on the other crankcase element by its upper edge. Sheathing, in free state, features axial size smaller than axial distance between attachment points of lower edge of inner shell and points of axial support of case of outer shell upper edge, when it is secured on crankcase. Another invention of proposed set relates to turbojet engine comprising above described crankcase sheathing.
EFFECT: ruling out of significant vibration strains in sheathing thanks to compensation of deviation between sheathing and crankcase thermal expansion.
6 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOJET ENGINE | 2004 |
|
RU2351771C2 |
| TURBO-JET ENGINE | 2004 |
|
RU2355894C2 |
| ATTACHMENT OF MULTISTAGE TURBOJET TO AIRCRAFT | 2009 |
|
RU2483004C2 |
| CYCLOIDAL REDUCER, FAN MODULE OF DUAL-FLOW TURBOJET ENGINE AND DUAL-FLOW TURBOJET ENGINE | 2013 |
|
RU2627990C2 |
| TURBOJET ENGINE UNLOADER, AND TURBOJET ENGINE WITH SAID UNLOADER | 2008 |
|
RU2467194C2 |
| FUEL INJECTION SYSTEM FOR TURBOJET ENGINE AND METHOD OF ITS ASSEMBLY | 2011 |
|
RU2578775C2 |
| DOUBLE-FLOW TURBOJET ENGINE WITH THE INTERMEDIATE JACKET, WITH THE DRIVE SHAFT OF TRANSFER GEARBOX FOR TURBOJET ENGINE ACCESSORY DRIVE | 2007 |
|
RU2442000C2 |
| TURBOJET ENGINE ONE-SHELL THRUST REVERSER | 1996 |
|
RU2145387C1 |
| NACELLE FOR BYPASS TURBOJET ENGINE | 2007 |
|
RU2440280C2 |
| DRIVE SHAFT OF GEAR BOX OF JET TURBINE ENGINE AUXILIARY MECHANISM | 2012 |
|
RU2582375C2 |
