Joseph J Simonetti

US Patent:

20130228647, Sep 5, 2013

Filed:

Mar 5, 2012

Appl. No.:

13/411782

Inventors:

Joseph Simonetti - Southbury CT, US
Matthew J. Tarascio - Milford CT, US
Michael Peter Strauss - New Haven CT, US
Adam Kasprzyk - Shelton CT, US
Timothy Fred Lauder - Oxford CT, US

Assignee:

SIKORSKY AIRCRAFT CORPORATION - Stratford CT

International Classification:

B64C 27/82
B64D 37/00
B64D 13/08
B64D 41/00
B64D 15/00

US Classification:

244 1721, 244 58, 244134 R

Abstract:

A rotary wing aircraft propulsion system includes an engine, a heat exchanger cooling a fluid from the engine and a thermoelectric generator in thermal communication with the fluid to generate electrical power. The thermoelectric generator provides electrical power to at least one aircraft component.

US Patent:

20130313371, Nov 28, 2013

Filed:

May 22, 2012

Appl. No.:

13/477376

Inventors:

Joseph Lawrence Simonetti - Southbury CT, US

Assignee:

SIKORSKY AIRCRAFT CORPORATION - Stratford CT

International Classification:

B64D 33/02

US Classification:

244 53 B

Abstract:

An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A method of operating an aircraft includes urging an inlet airflow into two or more duct openings disposed at a fuselage of the aircraft. The inlet airflow is urged through two or more converging inlet duct legs extending from the two or more duct openings toward an engine inlet. A portion of the inlet airflow is flowed from at least one inlet duct leg of the two or more inlet duct legs into a pressure relief pathway. An inlet duct for an engine or multiple engines includes one or more inlet duct legs and a bypass leg extending from an inlet duct leg of the one or more inlet duct legs through a bypass opening.

US Patent:

20180201386, Jul 19, 2018

Filed:

Jul 20, 2016

Appl. No.:

15/744422

Inventors:

- Stratford CT, US
Michael Joseph DeVita - Cos Cob CT, US
Joseph Lawrence Simonetti - Southbury CT, US
Carl A. Palmer - Pittsford NY, US

International Classification:

B64D 31/06
B64C 27/12
F02C 7/262
B64D 45/00
B64D 27/14

Abstract:

A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.

US Patent:

20180080380, Mar 22, 2018

Filed:

Mar 22, 2016

Appl. No.:

15/565275

Inventors:

- Stratford CT, US
Joseph Lawrence Simonetti - Southbury CT, US

International Classification:

F02C 7/042
B64D 27/10
B64D 35/08
F02C 7/26

Abstract:

A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable Stop engine inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.

US Patent:

20180016017, Jan 18, 2018

Filed:

Jul 10, 2017

Appl. No.:

15/645354

Inventors:

- Stratford CT, US
Joseph Lawrence Simonetti - Southbury CT, US
Nhan R. Tran - West Haven CT, US

International Classification:

B64D 13/06
F02C 9/18
F04F 5/20

Abstract:

A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air.

US Patent:

20170297732, Oct 19, 2017

Filed:

Oct 28, 2016

Appl. No.:

15/337327

Inventors:

- Stratford CT, US
Joseph Lawrence Simonetti - Southbury CT, US
Nicholas D. Lappos - Guilford CT, US
Jonathan Hartman - Lorton VA, US

International Classification:

B64D 31/12
B64D 27/10
B64D 27/24
B64D 27/02

Abstract:

The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.

US Patent:

20170089261, Mar 30, 2017

Filed:

Mar 4, 2014

Appl. No.:

15/122825

Inventors:

- Stratford CT, US
Joseph Lawrence Simonetti - Southbury CT, US

International Classification:

F02C 6/14
F02N 11/08
F01D 21/00
F01D 21/14
F01D 15/10
F02C 3/04

Abstract:

One aspect is an electrical augmentation system for a gas turbine engine. The electrical augmentation system includes an electric motor operably coupled to a shaft of the gas turbine engine, and an energy storage device operable to provide a temporary increased current source to the electric motor. The electrical augmentation system includes a control system having a torque demand anticipation circuit operable to determine an anticipated torque increase condition for the gas turbine engine. Based on the anticipated torque increase condition, the torque demand anticipation circuit commands a temporary torque increase by the electric motor using the energy storage device.