Patent Leaderboard
USPTO Patent Rankings Data through Dec 31, 2025
Home › Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies

Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies

US Patent 7665953 · Granted Feb 23, 2010

Estimated economic value: $64,181,000 ⓘ

Assignee

Inventors

View full patent text on Google Patents →

More Patents by These Inventors

Turbine vane in gas turbine engine2024
Turbine airfoil with trailing edge features and casting core2022
Cover plate with flow inducer and method for cooling turbine blades2022
Turbine blade with squealer tip and densified oxide dispersion strengthened laye2022
Turbine airfoil with trailing edge cooling featuring axial partition walls2022
Turbine airfoil with trailing edge framing features2021
Turbine rotor airfoil and corresponding method for reducing pressure loss in a c2021
Turbine rotor blade with airfoil cooling integrated with impingement platform co2021
Sealing arrangement between turbine shroud segments2021
Cooling configuration for a gas turbine engine airfoil2020
Gas turbine airfoil including integrated leading edge and tip cooling fluid pass2020
Shrouded turbine blade2020