Patrick Sean Sage, 75West Chester, OH

2018017, Jun 21, 2018

Dec 15, 2016

15/380176

- Schenectady NY, US
Patrick Sean Sage - West Chester OH, US

F02C 9/18
F02C 3/04
F02C 7/057
F02C 7/042
F01D 15/10

In one aspect, a power generation system may include a core turbine engine, an electric generator, an electric motor, and an auxiliary compressor. The core turbine engine defines an axial direction, and may include a compressor and a turbine in serial flow relationship along the axial direction. The electric generator may be operatively coupled to and driven by the core turbine engine. In addition, the electric motor may be in electrical communication with the electric generator for receiving electrical power generated by the electric generator. Furthermore, the auxiliary compressor may be positioned upstream of the compressor of the core turbine engine, and the auxiliary compressor may be rotatable by the electric motor to compress a volume of air to be provided to the compressor of the core turbine engine.

2018013, May 17, 2018

Nov 15, 2016

15/351738

- Schenectady NY, US
Ann Marie Yanosik - Liberty Township OH, US
Patrick Sean Sage - West Chester OH, US

F02C 7/143
F02C 7/16

A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.

2018010, Apr 12, 2018

Oct 7, 2016

15/287775

- Schenectady NY, US
Joseph George Rose - Mason OH, US
Patrick Sean Sage - West Chester OH, US
Jeffrey Donald Clements - Mason OH, US
Jeffrey Glover - Cincinnati OH, US

F02C 9/18
F04D 27/00
F04D 29/52
F01D 25/24
F02C 3/04
F01D 9/02

A gas turbine engine includes a casing surrounding a first compressor, as well as a liner extending forward from the first compressor. Additionally, the gas turbine engine includes a bleed air assembly having a plurality of bleed valves positioned in the liner and spaced along a circumferential direction of the gas turbine engine. The bleed air assembly also includes a duct in airflow communication with the plurality of bleed valves and defining an outlet at the casing. The duct provides a flow bleed air from the plurality bleed valves to the outlet during operation.

2018010, Apr 12, 2018

Oct 7, 2016

15/287782

- Schenectady NY, US
Joseph George Rose - Mason OH, US
Patrick Sean Sage - West Chester OH, US
Jeffrey Donald Clements - Mason OH, US
Jeffrey Glover - Cincinnati OH, US

F02C 9/18
F04D 27/00
F04D 29/52
F01D 25/24
F01D 9/02
F02C 3/04

A gas turbine engine includes a first compressor, a casing surrounding the first compressor, and a liner extending forward from the first compressor. The gas turbine engine also includes a core turbine frame assembly extending between the liner and the casing and a bleed air assembly. The bleed air assembly includes a bleed valve positioned in the liner, and a duct in airflow communication with the bleed valve and defining in outlet. The duct is positioned within the core turbine frame assembly and extends to the casing.