General Electric Company

Cathal Clancy

Daniel Edward Loringer

Rodrigo Rodriguez Erdmenger

Sebastian Walter Freund

Neil Xavier Blythe

Yu Du

Vittorio Michelassi

Jassin Marcel Fritz

Andrew Maxwell Peter

Lukas William Johnson

Florian Stefan Hoefler

Rudolf Konrad Selmeier

Matthias Carl Lang

Jonathan Nagurney

Pierre Sébastien Huck

Elisa Jubany Arribas

A turbine engine assembly includes a core compressor configured to discharge a first airflow at a first temperature and a first pressure. The turbine engine assembly also includes a cooling system turbine configured to receive the first airflow at the first temperature and the first pressure and discharge a second airflow at a second pressure less than the first pressure. The turbine engine assembly further includes a heat exchanger configured to receive the second airflow and discharge a third airflow at a second temperature less than the first temperature. The turbine engine assembly also includes a cooling system compressor rotatably coupled to the cooling system turbine. The cooling system compressor is configured to receive the third airflow and discharge a fourth airflow at a third pressure greater than the first pressure.

System and method for cooling a turbine engine assembly

The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Variable geometry nozzle and associated method of operation

An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.

Engine with improved EGR system

Growing community of inventors

Munich, Germany

Cathal Clancy