Compression section for an axial flow rotary machine
US4460309A · kind A · utility
12Cited by
10References
3Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Sep 27, 1982 |
| Grant date | Jul 17, 1984 |
| Priority date | — |
| Expiry date | Sep 27, 2002 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/541
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compression section of a gas turbine engine having an annular flow path is disclosed. Various construction details which increase the efficiency of an array of rotor blades in the compression section are developed. The annular flow path is contoured to cause the streamlines of the flow path to follow a pattern of varying radial curvature. In one embodiment, a conical surface extending between the base of each airfoil on the inner wall causes a flow path contraction and a cylindrical surface on the outer wall facing the tip of each airfoil enables close clearances.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.