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Ivett A Leyva

from College Station, TX
Age ~53
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Also known as:
Ivett Alejandra Leyva, Ivett A Leyra, Yvett A Leyva, Mett A Leyva, Ivett A Leyza, Ivett A Holm-Hansen
Related to:
Steven Holm-Hansen, 62Christian Holm-Hansen, 26Gary Holm-Hansen, 63
Connected to:
Abisai C Leyva, 31Adan R Leyva, 34Alberto A Leyva, 56Alex Leyva, 50Alfred Leyva, 33Amos E Leyva, 69Austin P Leyva, 44Belkys Leyva, 33Camila Leyva, 27Carmina B Leyva, 30

Ivett Leyva Phones & Addresses

  • College Station, TX
  • 3034 Sleepy Hollow Rd, Falls Church, VA 22042
  • 8180 Manitoba St, Playa del Rey, CA 90293
  • Marina del Rey, CA
  • Lancaster, CA
  • Niskayuna, NY
  • Pasadena, CA

Resumes

Resumes

Ivett Leyva Photo 1

Senior Aerospace Engineer

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Location:
3034 Sleepy Hollow Rd, Falls Church, VA 22042
Industry:
Aviation & Aerospace
Work:
Microcosm, Inc. 2005 - 2006
Propulsion Ipt
Ge 1999 - 2003
Mechanical Engineer
Caltech 1993 - 1999
Student
Caltech 1994 - 1999
Graduate Student
Air Force Research Laboratory 1994 - 1999
Senior Aerospace Engineer
Education:
Caltech 1992 - 1999
Skills:
Propulsion
Aerospace
Systems Engineering
Simulations
Engineering Management
Aerospace Engineering
Spacecraft
Aerodynamics
Matlab
Cfd
Sensors
Mechanical Engineering
Testing
Finite Element Analysis
Labview
Aeronautics
Ivett Leyva Photo 2

Ivett Leyva

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Publications

Us Patents

Shock Wave Reflector And Detonation Chamber

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US Patent:
6877310, Apr 12, 2005
Filed:
Mar 27, 2002
Appl. No.:
10/107653
Inventors:
Ivett Alejandra Leyva - Niskayuna NY, US
Assignee:
General Electric Company - Niskayuna NY
International Classification:
F02C005/00
US Classification:
60247, 60 3938, 60 3976, 431 1
Abstract:
A shock wave reflector includes a number of reflective units positioned along a longitudinal direction and separated by a gap G. Each reflective unit has a length L. The length L and the gap G are governed by a relationship L+G≧λ. The variable λ characterizes a cell size for a detonation mixture. A detonation chamber includes a receiving end, a discharge end, and a wall extending along a longitudinal direction between the receiving and discharge ends. The detonation chamber further includes a number of reflective units formed in the wall and positioned along the longitudinal direction. The reflective units are separated by a gap G, and each reflective unit has a length L.

Pulse Detonation System For A Gas Turbine Engine

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US Patent:
6889505, May 10, 2005
Filed:
Apr 2, 2003
Appl. No.:
10/405561
Inventors:
Lawrence Butler - Cincinnati OH, US
Kattalaicheri Srinivasan Venkataramani - West Chester OH, US
Kurt David Murrow - Indian Springs OH, US
Ivett Alejandra Leyva - Marina del Rey CA, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C005/00
US Classification:
60776, 602261, 60 3978
Abstract:
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate. Each detonation chamber includes a first open end located adjacent the outer circumferential surface of the cylindrical member and a second closed end located within a middle portion of the cylindrical member.

Two-Stage Pulse Detonation System

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US Patent:
6983586, Jan 10, 2006
Filed:
Dec 8, 2003
Appl. No.:
10/730219
Inventors:
Venkat Eswarlu Tangirala - Niskayuna NY, US
Anthony John Dean - Scotia NY, US
Ivett Alejandra Leyva - Los Angeles CA, US
Assignee:
General Electric Company - Niskayuna NY
International Classification:
F23R 7/00
US Classification:
60 3977, 602261, 60247, 60249, 60762
Abstract:
A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions for detonation initiation. A mixture of a fuel and a gas is burned in the pre-combustor and is passed through the nozzle into the geometric resonator, where the burned mixture is detonated. The detonation propagates through the resonator exit nozzle thus generating thrust.

Aircraft And Detonative Engine Incorporating Pulse Detonation Engines

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US Patent:
7093794, Aug 22, 2006
Filed:
Nov 22, 2002
Appl. No.:
10/065815
Inventors:
Ivett Alejancra Leyva - Niskayuna NY, US
Anthony John Dean - Scotia NY, US
Assignee:
General Electric Company - Niskayuna NY
International Classification:
B64D 27/18
US Classification:
244 54, 60 3976, 244 62
Abstract:
An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine is adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to the aircraft. At least one of the pulse detonation engines is movably configured for altering a direction of the thrust force relative to the airfoil.

Fuel Preconditioning For Detonation Combustion

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US Patent:
7690191, Apr 6, 2010
Filed:
Jan 6, 2006
Appl. No.:
11/326718
Inventors:
Anthony John Dean - Scotia NY, US
Ivett Alejandra Leyva - Playa Del Rey CA, US
Chukwueloka Obiora Umeh - Schenectady NY, US
Assignee:
General Electric Company - Niskayuna NY
International Classification:
F02K 5/02
US Classification:
60247, 60 3938, 60 3976
Abstract:
A fuel preconditioning system for use with a pulse detonation combustor (PDC) makes use of a heat source to pyrolyze fuel prior to injecting it into the PDC for detonation. The fuel is decomposed into a more detonable form by pyrolysis in a conditioner that applies heat to the fuel in the absence of oxidizer. The heat may be provided by a hot section of the engine, including the walls of the PDC itself. The conditioned fuel is fed to the PDC and detonated.

Method And Apparatus For Generating Torque

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US Patent:
20040000145, Jan 1, 2004
Filed:
Jun 27, 2002
Appl. No.:
10/184241
Inventors:
Ivett Leyva - Niskayuna NY, US
Anthony Dean - Scotia NY, US
Bernard Robic - Niskayuna NY, US
Lawrence Butler - Cincinnati OH, US
International Classification:
F02C003/16
US Classification:
060/772000, 060/039340
Abstract:
An apparatus for generating torque, the apparatus comprising: a rotor hub adapted for applying torque to a shaft; and a plurality of pulse detonation engines adapted for impulsively detonating a plurality of fuel/air mixtures to generate thrust forces and applying the thrust forces to the rotor hub to generate the torque.

Method And Apparatus For Lifting And Propelling Rotorcraft

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US Patent:
20040000614, Jan 1, 2004
Filed:
Jun 27, 2002
Appl. No.:
10/184240
Inventors:
Ivett Leyva - Niskayuna NY, US
Anthony Dean - Scotia NY, US
Bernard Robic - Niskayuna NY, US
Lawrence Butler - Cincinnati OH, US
International Classification:
B64C027/00
US Classification:
244/017110
Abstract:
An apparatus for lifting and propelling a rotorcraft, the apparatus comprising: a rotor hub adapted for applying lift and propulsive forces to the rotorcraft; a plurality of rotor blades mechanically coupled to the rotor hub to form a rotor assembly and adapted for generating the lift and propulsive forces; and a plurality of pulse detonation engines adapted for impulsively detonating a plurality of fuel/air mixtures to generate thrust forces and applying the thrust forces to the rotor assembly.

Pulse Detonation Power System And Plant With Fuel Preconditioning

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US Patent:
20050109010, May 26, 2005
Filed:
Nov 25, 2003
Appl. No.:
10/723319
Inventors:
Anthony Dean - Scotia NY, US
Ivett Leyva - Los Angeles CA, US
International Classification:
F02C005/00
US Classification:
060039760
Abstract:
A power system includes a fuel preconditioner adapted to convert a fuel to at least one conditioned fuel, a pulse detonation combustor, and a turbine. The pulse detonation combustor is adapted to receive the conditioned fuel and a primary oxidizer and to detonate a mixture including the conditioned fuel and the primary oxidizer and exhaust a number of detonation products. The turbine is positioned downstream from and in flow communication with the pulse detonation combustor. A power plant includes at least one fuel preconditioner and a number of power systems. Each power system includes a pulse detonation combustor and a turbine positioned downstream from and in flow communication with the pulse detonation combustor.
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Ivett A Leyva from College Station, TX, age ~53 Get Report