Hamilton Sundstrand Corporation

Sundstrand Corporation

Amylin Pharmaceuticals, Inc.

Other

United Technologies Corporation

Robert G Thompson

Michael K Sahm

James C Napier

Orville G Kolterman

Jose Albero

Richard Dussault

John F Mullane

Jack R Shekleton

Louis J Bruno

Charles E Lents

Colin Rodgers

Eric Tremaine

Patrick Germain

Wayne A Thresher

Nipulkumar Shah

Bezhad Hagshenas

An adjustment method and system for an auxiliary power unit (APU) allows the APU speed to vary based on the inlet air temperature to the APU compressor. The APU is controlled by a control law that allows the APU speed to float within a selected range based on speed and electric power generators phase matching criteria that provides smooth power transfer between the APU and a main engine generator. The specific APU mechanical speed for a given temperature may be determined from a compressor map that identifies the optimum combination of pressure ratio, flow rate and efficiency for a given inlet temperature, and avoids running the APU near mechanical resonant vibration conditions.

Auxiliary power unit control method and system

An auxiliary power unit (APU) inlet muff anti-icing system that uses high pressure, high temperature APU compressor delivery air to melt any accumulation of ice and snow near the bottom of the muff with a tracer line coupled to a perforated gull wing fairing mounted within the inlet muff and that uses the compressor delivery air as the primary stream for an ejector to suck ice and snow melt accumulating near the fairing overboard.

Inlet muff anti-icing system for an auxiliary power unit

A main engine electric start system for gas turbine propelled aircraft that employs a low-power AC electrical power system to serve as an independent grid to control the functions of induction-type dynamoelectric machines coupled to the main propulsion engines and APU as a starter or generator.

Main engine electric start system

A starting system for starting the propulsion engines of gas turbine powered aircraft that combines power sources delivered by the APU so that essentially then entire power delivered by the APU for pneumatic, hydraulic and electric power is applied to corresponding starters on each propulsion engine during MES simultaneously.

Combined power main engine start system

An auxiliary power unit for aircraft with a load compressor that delivers cabin air free of oil contamination by supporting a drive shaft for the load compressor with oil-free bearings and coupling the load compressor to a gearbox and power head for the auxiliary power unit through a synchronous magnetic torque coupling on an opposite side of the gearbox to which the power is mounted.

Auxiliary power unit with an oil-free compressor

A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.

Main propulsion engine system integrated with secondary power unit

An APU system includes a gas turbine engine having a low pressure spool, a high pressure spool and an electrical generator. The electrical generator is driven by the high pressure spool which is governed to a constant speed. Conversely, the low pressure spool is not governed at all, but is allowed to seek a speed that balances the power developed by the low pressure turbine (LPT) and power absorbed by the low pressure compressor (LPC). A step increase/decrease in electrical power demand is met with a step increase/decrease in fuel flow, which results in an overshoot/undershoot of the new equilibrium turbine inlet temperature TIT. The TIT returns to the new equilibrium when the LP spool has achieved it's new shaft speed and new equilibrium power balance. The HP Spool and generator maintain essentially constant speed and frequency, while the LP Spool responds to restore equilibrium. The APU's response to sudden power change is thereby effectively immediate as the power change is decoupled from the large mechanical inertia of the HP and LP spools.

Turbocharged auxiliary power unit with controlled high speed spool

An integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

Aircraft system architecture

Methods for treating non-insulin-taking Type II diabetes mellitus which comprise administering a therapeutically effective amount of an amylin agonist.

Treatment of type II diabetes mellitus with amylin agonists

Increased efficiency of operation in pressurized aircraft may be obtained by employing pressurized air to be discharged from an aircraft cabin,as combustion air by applying it to the inlet,of a cycle compressor,whereat it is compressed before being fed to a combustor,. Fuel from a source,is combusted within the combustor,and drives a high pressure turbine,as well as a low pressure turbine,, either one of which may drive a load,to provide electrical power for the aircraft. In addition, a load compressor,provides air to an environmental control system including an ECS turbo machine,and a bypass,for delivering conditioned air to the cabin

Secondary power integrated cabin energy system for a pressurized aircraft

Treatment of Type II diabetes mellutis with amylin agonists

In order to reduce noise transmission through the air inlet duct (16) of a turbine engine (10), the air inlet duct (16) provides a non-linear path defined by a bend (24) for air from a source, and the turbine engine (10) includes a sound attenuation assembly (26) in the form of a splitter dissipative silencer disposed near the bend (24) in the air inlet duct (16). More specifically, the turbine engine (10) is such that the splitter dissipative silencer (26) can be formed as a modular assembly (42) removably securable near the bend (24) in the air inlet duct (16) upstream of a radial compressor (12) for removal and/or replacement or availability as an optional component of the turbine engine (10).

Turbine inlet silencer

In order to provide an expansive central recirculating gas zone (40) in a combustor (10), and in a manner wherein the combustion chamber (20) is of compact volume, a stored energy combustor (10) comprises a vessel (12) having narrow, spaced-apart inlet and outlet ends (14, 16) interconnected by a wall (18) defining a relatively wise combustion chamber (20). The combustion chamber (20) is generally annular and a wall (18) defining the combustion chamber (20) includes an upstream wall region (18a) and a downstream wall region (18c) interconnected by a generally annular side wall region (18b). The inlet end (14) and outlet end (16) are generally tubular extensions of the vessel (12) leading to and from the combustion chamber (20) and oxidant is swirled in the tubular extension (14) leading to the combustion chamber (20) and directed in a swirling annulus into the combustion chamber (20) outwardly of a fuel injector (28). The combustion chamber (20) is formed such that at least the upstream wall region (18a) has an inner surface of gentle radius joining the generally annular side wall region (18b) to the tubular extension (14) of the vessel (12) leading to the combustion chamber (20). With this arrangement, the swirling oxidant annulus expands radially outwardly in a generally conical fashion within the combustion chamber (20) upon exiting the tubular extension (14) while sticking to at least the upstream wall region (18a) of the wall (18) defining the combustion chamber (20).

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San Diego, CA, United States of America

Robert G Thompson