Joseph T Rose

US Patent:

20210372327, Dec 2, 2021

Filed:

Jan 14, 2021

Appl. No.:

17/148859

Inventors:

- Schenectady NY, US
Jeff Glover - Cincinnati OH, US
Joseph Rose - Mason OH, US
Jeffrey Donald Clements - Mason OH, US

International Classification:

F02C 7/18
F01D 25/24

Abstract:

A turbine engine including a core engine cowl including a compartment, and a cooling system positioned within the compartment. The cooling system includes a cooling fan configured to exhaust heat from the compartment, a temperature sensor configured to monitor a temperature within the compartment, and a controller coupled in communication with the cooling fan and the temperature sensor. The controller is configured to actuate the cooling fan when the temperature is greater than a threshold.

US Patent:

20180362170, Dec 20, 2018

Filed:

Jun 14, 2017

Appl. No.:

15/622290

Inventors:

- Schenectady NY, US
Thomas Ory Moniz - Loveland OH, US
Jeffrey Donald Clements - Mason OH, US
Joseph George Rose - Mason OH, US

International Classification:

B64D 27/26
B64D 27/12
B64D 29/02

Abstract:

A system for mounting an engine to an aircraft includes an engine forward mount angled toward the forward end of the engine at a first angle. At least two thrust links extend between an engine aft mount to a link support connection at a second angle. The engine aft mount is angled toward the forward end of the engine at a third angle. A projection of a load vector of the engine forward mount onto a vertical plane extending through the axis of rotation of the engine and a projection of a load vector of each of the at least two thrust links onto the vertical plane intersect the axis of rotation of the engine within a first vertical plane segment extending between a forward end of a nose of a fan assembly and forward of a forward mount interface.

US Patent:

20180171816, Jun 21, 2018

Filed:

Dec 19, 2016

Appl. No.:

15/382817

Inventors:

- Schenectady NY, US
Joseph George Rose - Mason OH, US
Robert Harold Weisgerber - Loveland OH, US
Jeffrey Donald Clements - Mason OH, US
Brandon Wayne Miller - Liberty Township OH, US

International Classification:

F01D 17/04
F02K 3/06
F02C 7/36

Abstract:

A gas turbine engine includes a fan section having a fan rotatable with a fan shaft and a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine. A power gearbox is also provided mechanically coupled to both the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox. A torque monitoring system includes a gearbox sensor operable with a gear of the power gearbox and a shaft sensor operable with at least one of the turbomachine shaft or the fan shaft. The torque monitoring system determines an angular position of the gear of the gearbox relative to at least one of the fan shaft or the turbomachine shaft using the gearbox sensor and the shaft sensor to determine a torque within the gas turbine engine.

US Patent:

20180149086, May 31, 2018

Filed:

Nov 29, 2016

Appl. No.:

15/363569

Inventors:

- Schenectady NY, US
Jeff Glover - Cincinnati OH, US
Joseph Rose - Mason OH, US
Jeffrey Donald Clements - Mason OH, US

International Classification:

F02C 7/18

Abstract:

A turbine engine including a core engine cowl including a compartment, and a cooling system positioned within the compartment. The cooling system includes a cooling fan configured to exhaust heat from the compartment, a temperature sensor configured to monitor a temperature within the compartment, and a controller coupled in communication with the cooling fan and the temperature sensor. The controller is configured to actuate the cooling fan when the temperature is greater than a threshold.

US Patent:

20180149093, May 31, 2018

Filed:

Nov 29, 2016

Appl. No.:

15/363530

Inventors:

- Schenectady NY, US
Jeff Glover - Cincinnati OH, US
Joseph Rose - Mason OH, US
Jeffrey Donald Clements - Mason OH, US

International Classification:

F02C 9/18
F02C 3/04
F01D 25/24
F02K 3/06
F02C 7/18

Abstract:

A turbine engine including a core engine cowl including a compartment, a cooling airflow source positioned within the compartment, and a full authority digital engine control (FADEC) system coupled in communication with the cooling airflow source. The FADEC system is configured to determine a flight status of the turbine engine, and actuate the cooling airflow source when the turbine engine is not in flight, and before the turbine engine has been shut down, such that heat is exhausted from the compartment.

US Patent:

20180100435, Apr 12, 2018

Filed:

Oct 6, 2016

Appl. No.:

15/286621

Inventors:

- Schenectady NY, US
Joseph George Rose - Mason OH, US
Jeffrey Donald Clements - Mason OH, US

International Classification:

F02C 7/06
F02K 3/06
F02C 3/04

Abstract:

A gas turbine engine includes a low pressure compressor and a low pressure turbine, with a low pressure shaft coupled to the low pressure turbine through a turbine extension and coupled to the low pressure compressor through a compressor extension. A forward bearing assembly supports the low pressure shaft within a compressor section and at a location aft of the compressor extension and an aft LP bearing assembly supports the low pressure shaft within a turbine section at a location aft of the turbine extension.

US Patent:

20180100440, Apr 12, 2018

Filed:

Oct 7, 2016

Appl. No.:

15/287775

Inventors:

- 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

International Classification:

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

Abstract:

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.

US Patent:

20180100441, Apr 12, 2018

Filed:

Oct 7, 2016

Appl. No.:

15/287782

Inventors:

- 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

International Classification:

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

Abstract:

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.