Turbine nozzle support arrangement
US5271714A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jul 9, 1992 |
| Grant date | Dec 21, 1993 |
| Priority date | — |
| Expiry date | Jul 9, 2012 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine engine having an annular casing with a stationary support structure, a high pressure turbine, and an annular high pressure turbine nozzle having at least one stage which includes a plurality of circumferentially aligned nozzle segments and which is disposed in the annular casing between a combustor and the high pressure turbine, a nozzle support arrangement is provided for mounting each nozzle segment to the stationary support structure. The arrangement includes a single mounting pin mounted on and extending from an annular nozzle support flange on the casing support structure and a hole defined in an oval shape in the one end portion of an inner band flange for receiving the mounting pin in an interference fitting relation. The oval-shaped hole has a greater height than width such that a tight tangential fit of the pin with the hole is provided along the width of the hole and a loose fit of the pin with the hole is provided along the height of the hole so as to ensure negligible variation of the tangential location of the nozzle segments relative to one another and to the support structure, while allowing free axial rocking of the nozzle segment on the inner band …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.