Mid-frame section of a gas turbine engine and corresponding method of adjusting radial rotor clearance
US12116927B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2018 |
| Grant date | Oct 15, 2024 |
| Priority date | — |
| Expiry date | Jun 18, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A mid-frame section of a gas turbine engine having a radial clearance adjustability and a method for adjusting a radial clearance to a rotor in a mid-frame section of a gas turbine engine are presented. The mid-frame section includes a radial clearance adjusting assembly arranged at a compressor exit diffusor. The radial clearance adjusting assembly is configured to adjust the radial clearance to the rotor such that the rotor is concentric with respect to components of the mid-frame section, such as the compressor exit diffusor and shaft cover. The radial clearance adjusting assembly provides radial clearance adjustability in the mid-frame section at multiple locations, such as at forward end and aft end of the compressor exit diffusor. The radial clearance adjusting assembly improves efficiency of the gas turbine and reduces service and operating cost of the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.