Patrick J Lonneman, Age 786352 Upper Rd, Cincinnati, OH 45233

2016036, Dec 22, 2016

Jun 22, 2015

14/746426

- Schenectady NY, US
Darek Tomasz Zatorski - Fort Wright KY, US
Tsuguji Nakano - West Chester OH, US
Patrick John Lonneman - Erlanger KY, US

F01D 7/00
F01D 15/00
F01D 5/30
F02C 3/04
F01D 5/02
F01D 25/24

An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.

2016033, Nov 17, 2016

May 4, 2016

15/145894

- Schenectady NY, US
Andrew BREEZE-STRINGFELLOW - Cincinnati OH, US
Richard David CEDAR - Cincinnati OH, US
Syed Arif KHALID - West Chester OH, US
Patrick John LONNEMAN - Erlanger KY, US
Aleksander Piotr PASIECZNY - Warsaw, PL
Daniel Lawrence TWEEDT - West Chester OH, US

F01D 25/04
F01D 5/02
F01D 25/24
F01D 9/04
F04D 29/32
F04D 29/38

An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.

2016014, May 26, 2016

Oct 2, 2015

14/873324

- Schenectady NY, US
Patrick John LONNEMAN - Erlanger KY, US
Alan Roy STUART - Cincinnati OH, US

F02C 9/16
F02K 3/06

A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct for airflow generated by the fan. The fan cowl includes an aft edge that defines a physical flow area of the bypass duct, and a deflection device configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.

2016014, May 26, 2016

Nov 13, 2015

14/940543

- Schenectady NY, US
Patrick John LONNEMAN - Erlanger KY, US

F02K 1/72
F04D 27/00
F04D 19/00

A gas turbine engine having a centerline axis is provided. The gas turbine engine includes a fan and a fan cowl assembly surrounding the fan to define a bypass duct configured to channel airflow for the fan. The fan cowl assembly includes a stationary cowl and a transcowl. The gas turbine engine further includes a plurality of actuators configured for displacing the transcowl relative to the stationary cowl. Each of the actuators is skewed relative to the centerline axis of the engine.