#F01D17/02

SYSTEM FOR ACTIVE DATA ACQUISITION MANAGEMENT IN A GAS TURBINE ENGINE

An aircraft sensor system (100) includes a first sensor (90; 110; 430) configured to detect a parameter of an aircraft system and a first micro electromechanical-system (MEMS) (120, 122, 124, 126, 128…

DRIVE·Apr 8·2 min read

F01D17/02 RTX CORP [US]

ELECTRICAL CONNECTIVITY TO HIGH TEMPERATURE FILM SENSOR DEVICES

The present disclosure provides for electrical connectivity to high temperature film sensor devices (e.g., temperature sensor devices). More particularly, the present disclosure provides for high temp…

DRIVE·Sep 3·2 min read

F01D17/02 UNIV OF RHODE ISLAND BOARD OF TRUSTEES [US]

SYSTEM AND METHOD FOR REMOVABLY INSERTING A SENSOR ASSEMBLY INTO A COMPRESSOR CASING

A measurement system (13) for a gas turbine engine (11) is provided. The measurement system (13) comprises a sensor assembly (48). The measurement system (13) also includes multiple sensors (64) coupl…

DRIVE·Nov 27·1 min read

F01D17/02 GENERAL ELECTRIC TECHNOLOGY GMBH [CH]

THERMAL PROTECTION FOR A GAS TURBINE ENGINE PROBE

A thermal shielding arrangement for a turbine probe (22) comprises a heat shield having first and second mating portions (40, 42) axially engaged in overlapping relationship around a probe (22) extend…

DRIVE·Jul 3·1 min read

F01D17/02 PRATT & WHITNEY CANADA [CA]

INTERNAL MOTOR HEATING OPERATION BY INCREASING LOAD

The invention relates to an operating method for a device comprising an internal combustion engine with a crankshaft and multiple cylinders and an exhaust aftertreatment system. The operating method i…

DRIVE·Jan 11·1 min read

F01D17/02 MAN TRUCK & BUS AG [DE]

Aircraft gas turbine engine with a first rotatable shaft

The aircraft gas turbine (1) has a first rotating shaft (16), through which torque is interchanged between the two units, and a coaxial-arranged second shaft (17), which is rotationally connected to a…

DRIVE·Aug 27·1 min read

F01D17/02 ROLLS ROYCE DEUTSCHLAND [DE]

Aircraft jet engine system for optimizing power usage from damaged fan blades and corresponding method

An aircraft jet engine system includes at least one gas turbine engine (10) having a fan (14) including a rotor and a plurality of fan blades (100). A sensor system (102, 104) in the fan section (14) …

DRIVE·May 8·2 min read

F01D17/02 UNITED TECHNOLOGIES CORP [US]

A controller, for use in a power plant having a liquid cooling system and an air cooling system

A controller, for use in a power plant having a liquid cooling system and an air cooling system, comprising one or more inputs, configured to receive a signal from at least one deposit sensor, wherein…

DRIVE·Nov 14·1 min read

F01D17/02 ROLLS ROYCE PLC [GB]

System for observing combustion conditions in a gas turbine

A system for stabilizing combustion in a gas turbine engine comprises a) optical sensing means embedded within a fuel injector for observing conditions within a combustion chamber of a gas turbine eng…

DRIVE·Oct 10·1 min read

F01D17/02 ROSEMOUNT AEROSPACE INC [US]

A Transducer Assembly

A transducer assembly (100) for connecting a transducer (102) to a device, the transducer assembly comprising: a transducer mount (110) adapted to receive the transducer; and a clamp (120) comprising …

DRIVE·Jun 22·1 min read

F01D17/02 ROLLS ROYCE PLC [GB]

An apparatus and method of operating a gas turbine engine

A gas turbine engine (10) and an apparatus for operating the gas turbine engine (10) comprises at least one microphone (62) to detect the sound of impacts of particles on a surface of the gas turbine …

DRIVE·Apr 6·2 min read

F01D17/02 ROLLS ROYCE PLC [GB]

Method for inspecting the dynamic operation of an exhaust gas turbo-charger

The method involves providing a definite hot gas mass flow with a definite time-dependent pressure pulses. A turbine of an exhaust turbo charger is operated using a pressure pulse hot gas mass flow in…

DRIVE·Apr 6·1 min read

F01D17/02 CONTINENTAL AUTOMOTIVE GMBH [DE]

Apparatus and method for observing combustion conditions in a gas turbine engine

A fuel injector for a gas turbine combustor is disclosed which includes a feed arm (22) having a flange (24) for mounting the injector within the combustor and a fuel nozzle (26) depending from the fe…

DRIVE·Nov 9·1 min read

F01D17/02 ROSEMOUNT AEROSPACE INC [US]

Gas turbine with control box mounting device

The gas turbine, especially an aviation jet engine (10), has at least one ancillary unit (14) fastened to it and receiving signals from at least one sub-unit of the gas turbine. The ancillary unit has…

DRIVE·Dec 15·1 min read

F01D17/02 MTU AERO ENGINES GMBH [DE]

Fuel ratio control method in a gas turbine combustor

A fuel ratio control method and a device therefor in a gas turbine combustor are provided in which supply ratio of pilot fuel to main fuel is appropriately maintained to thereby avoid unstable combust…

DRIVE·Apr 9·2 min read

F01D17/02 MITSUBISHI HEAVY IND LTD [JP]

Method and apparatus for characterizing a combustion flame

A method of detecting an amount of a contaminant in an enclosure, the method comprising: detecting (S7) a first amplitude of energy within a first wavelength band of a first width centered about an em…

DRIVE·Apr 2·1 min read

F01D17/02 MEGGITT AVIONICS INC [US]

Methods for operating gas turbine engines

A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The f…

DRIVE·Sep 18·1 min read

F01D17/02 GEN ELECTRIC [US]