GEORGE WEBSTER BRALY
Pilots at Kings Rd, Ada, OK
License number
Oklahoma A0201902
Issued Date
May 2016
Expiration Date
May 2017
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
331 W Kings Rd, Ada, OK 74820
Professional information
Emergency Descent Intervention System
US Patent:
8504222, Aug 6, 2013
Filed:
Sep 10, 2010
Appl. No.:
12/880054
Inventors:
George W. Braly - Ada OK, US
Timothy Roehl - Ada OK, US
Timothy Roehl - Ada OK, US
International Classification:
G05D 1/00
US Classification:
701 4, 701 3, 701 5, 701 9
Abstract:
An emergency descent system for turbocharged piston engine powered aircraft. The flight management system is configured to challenge the pilot after a period of inactivity. Acknowledgment from the pilot resets the timer for subsequent challenge. Lack of timely pilot response sets off an alarm sequence. Lack of response to the alarm sequence sets off emergency descent by way of control by the flight management system of rate of descent, heading, ground track, and engine power by adjustment to the wastegate to the turbocharger. The control by the flight management system may incorporate direct control of the aircraft airspeed in the descent, and that may be enhanced by engine power adjustments. Upon reaching a selected target altitude, the aircraft engine power may be restored via the adjustment of the wastegate controller. At any time, when the pilot regains useful consciousness, the entire emergency descent sequence may be interrupted and normal control restored by the pilot.
Optimizing The Efficiency Of An Internal Combustion Engine
US Patent:
5941222, Aug 24, 1999
Filed:
Jan 6, 1998
Appl. No.:
9/003190
Inventors:
George W. Braly - Ada OK
Assignee:
General Aviation Modifications, Inc. - Ada OK
International Classification:
F02D 4100
US Classification:
123676
Abstract:
A fuel injector matrix to optimize the operating efficiency of an internal combustion engine, each injector having a metering orifice sized for each of the combustion cylinders of the engine to provide a uniform fuel to air ratio to all the cylinders such that all the cylinders reach a peak exhaust gas temperature at a common total engine fuel flow.
Full Time Lean Running Aircraft Piston Engine
US Patent:
2012025, Oct 11, 2012
Filed:
Jun 20, 2012
Appl. No.:
13/528113
Inventors:
George W. BRALY - Ada OK, US
International Classification:
F02B 1/02
US Classification:
244 59
Abstract:
A full time lean air fuel mixture running spark ignited air cooled aircraft piston engine. In one embodiment, a drop-in substitution is provided for an equivalent make, model, and engine size, wherein the new, rebuilt, or reconfigured engine provides as much or more horsepower when compared to the original engine, but runs at a lean air fuel ratio condition during normal operating modes, including takeoff, climb, and cruise, thus saving significantly on fuel. In yet another embodiment, a drop-in substitution having a somewhat larger cylinder displacement volume may be provided to attain equivalent or enhanced maximum horsepower while operating at lean air fuel ratios.Enhanced engine life may be anticipated, since cylinder head temperatures (CHTs) may be reduced, compared to engines using rich air fuel ratios for climb and cruise conditions. Aircraft using such engines are also disclosed.
Full Time Lean Running Aircraft Piston Engine
US Patent:
8205331, Jun 26, 2012
Filed:
Jan 26, 2009
Appl. No.:
12/359984
Inventors:
George W. Braly - Ada OK, US
International Classification:
B64D 27/04
US Classification:
29888011, 244 53 R, 244 54, 244 55
Abstract:
A full time lean air fuel mixture running spark ignited air cooled aircraft piston engine. In one embodiment, a drop-in substitution is provided for an equivalent make, model, and engine size, wherein the new, rebuilt, or reconfigured engine provides as much or more horsepower when compared to the original engine, but runs at a lean air fuel ratio condition during normal operating modes, including takeoff, climb, and cruise, thus saving significantly on fuel. In yet another embodiment, a drop-in substitution having a somewhat larger cylinder displacement volume may be provided to attain equivalent or enhanced maximum horsepower while operating at lean air fuel ratios. Enhanced engine life may be anticipated, since cylinder head temperatures (CHTs) may be reduced, compared to engines using rich air fuel ratios for climb and cruise conditions. Aircraft using such engines are also disclosed.
High Octane Unleaded Aviation Fuel
US Patent:
8628594, Jan 14, 2014
Filed:
Dec 1, 2010
Appl. No.:
12/958390
Inventors:
George W. Braly - Ada OK, US
International Classification:
C10L 1/22
US Classification:
44426
Abstract:
An unleaded aviation fuel blend. The fuel blend is provided by blending an unleaded aviation gasoline base fuel which may include iso-octane and iso-pentane, and an effective amount of a selected alkyl benzene to improve the functional engine performance to avoid harmful detonation sufficient to meet or exceed selected standards for detonation performance requirements in full scale aircraft piston spark ignition engines designed for use with Grade 100LL avgas. Advantageous alkylated benzenes include those having a meta-ring position between alkyl groups. Alkyl groups may be provided at least in part by methyl groups. In an embodiment, the alkyl benzene may include 1,3-dimethylbenzene. In an embodiment, two or more alkylated benzenes may be provided. In an embodiment, 1,3,5-trimethylbenzene may be provided. Suitable alkylated benzenes may include a mixture of xylene isomers.
Enhancement And Extension Of Structural Integrity Of Aircraft Structure
US Patent:
7658348, Feb 9, 2010
Filed:
May 22, 2006
Appl. No.:
11/438731
Inventors:
George W. Braly - Ada OK, US
International Classification:
B64C 1/26
US Classification:
244119, 244131
Abstract:
A method and apparatus for modifying aircraft having a fuselage and center fuselage carry through structure that support wing structures, comprising placing a load transferring member to extend through the center fuselage carry through structure, and transferring the tension loads from the wing structures to the center fuselage carry through structure so as to provide a redundant load path that is resistant to the hazards of single point failures modes.
Computer-Generated Icon And Portion Of An Engine Instrument Display
US Patent:
D563977, Mar 11, 2008
Filed:
Jul 20, 2006
Appl. No.:
29/263354
Inventors:
Wayne H. Carl - Canandaigua NY, US
Susan A. Dalton - Farmington NY, US
Eric C. Hathaway - Macedon NY, US
Walter Atkinson - Baton Rouge LA, US
George Webster Braly - Ada OK, US
Susan A. Dalton - Farmington NY, US
Eric C. Hathaway - Macedon NY, US
Walter Atkinson - Baton Rouge LA, US
George Webster Braly - Ada OK, US
Assignee:
Xerion Avionix, LLC - Pittsford NY
International Classification:
1404
US Classification:
D14488