Cooling system of a stator assembly for a gas turbine engine having a variable cooling flow mechanism and method of operation
US10094229B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 28, 2015 |
| Grant date | Oct 9, 2018 |
| Priority date | — |
| Expiry date | Mar 11, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system integrated into a stator assembly of a gas turbine engine has an on-board injector or cooling nozzle located for cooling of a rotor assembly. The nozzle may be generally annular and may contain a plurality of pivoting airfoils circumferentially spaced from one-another for directing cooling air flow from the nozzle and generally toward a plurality of holes in a cover of the rotor assembly. The pivoting airfoils are adapted to move between a spoiled state where the mass flow of cooling air is reduced, and to an optimal state where the mass flow is increased. The system may further include a plurality of fixed airfoils in the nozzle with adjacent fixed airfoils defining a discharge orifice in the nozzle. Each one of the plurality of pivoting airfoils may be located in a respective discharge orifice.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.