Trajaen J Troia

US Patent:

20110036067, Feb 17, 2011

Filed:

Aug 11, 2009

Appl. No.:

12/539451

Inventors:

George D. Rupp - Lakewood CA, US
Trajaen J. Troia - Hermosa Beach CA, US

International Classification:

F02K 3/02

US Classification:

602261, 60204

Abstract:

The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.

US Patent:

20110138814, Jun 16, 2011

Filed:

Dec 11, 2009

Appl. No.:

12/636579

Inventors:

George D. Rupp - Lakewood CA, US
Trajaen J. Troia - Hermosa Beach CA, US

International Classification:

F02C 1/00
F02C 9/00

US Classification:

60772, 60794

Abstract:

The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude. Calculating an efficient amount of airflow to provide to the DTSA turbine blades thorough a decoupled airstream; and directing movement of a modulator vane located in the intake duct to vary airflow to the DTSA turbine.

US Patent:

20130177392, Jul 11, 2013

Filed:

Feb 28, 2013

Appl. No.:

13/781584

Inventors:

Northrop Grumman Corporation - Falls Church VA, US
Trajaen J. Troia - Hermosa Beach CA, US

Assignee:

NORTHROP GRUMMAN CORPORATION - Falls Church VA

International Classification:

F04D 3/00

US Classification:

415 1

Abstract:

The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.

US Patent:

20150377060, Dec 31, 2015

Filed:

Jul 7, 2015

Appl. No.:

14/793377

Inventors:

- Falls Church VA, US
Trajaen J. Troia - Hermosa Beach CA, US

International Classification:

F01D 17/12
F01D 5/02
F01D 9/04

Abstract:

The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.

US Patent:

20140259631, Sep 18, 2014

Filed:

Mar 15, 2013

Appl. No.:

13/842567

Inventors:

NORTHROP GRUMMAN SYSTEMS CORPORATION - , US
Gordon Hall - Mammoth Lakes CA, US
Kelly Strominger - Hawthorne CA, US
John Tapee - Redondo Beach CA, US
Trajaen J. Troia - Hermosa Beach CA, US

Assignee:

NORTHROP GRUMMAN SYSTEMS CORPORATION - Falls Church VA

International Classification:

F02K 1/00

US Classification:

29592

Abstract:

The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer function. The nozzle throat input and output angles are determined and used to define an initial portion of the nozzle primary stream lower expansion surface. The nozzle primary stream upper expansion surface and an aft portion of the primary stream lower expansion surface are defined using a method of characteristics. Initial and aft portions of the primary stream lower expansion surface are then connected by a straight line to define the primary stream nozzle.