Inventor

LORD WESLEY K

US78 patents

⚠️ This page may combine multiple inventors who share the name “LORD WESLEY K”. Patents are grouped by organization below to help distinguish them — per-person disambiguation is on the roadmap.

LORD WESLEY K

UNITED TECHNOLOGIES CORP

Reduced noise fan exit guide vane configuration for turbofan engines

Passively driven acoustic jet controlling boundary layers

Centrifugal air flow control

Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts

Gas turbine engine jet noise suppressor

Double lobed mixer with major and minor lobes

Fixed geometry mixer/ejector suppression system for turbofan aircraft engines

Geared gas turbine engine with reduced fan noise

Geared gas turbine engine with reduced fan noise

Turbine section of high bypass turbofan

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

Variable-shape variable-stagger inlet guide vane flap

Airfoil acoustic impedance control

Airfoil surface impedance modification for noise reduction in turbofan engines

Method of noise suppression for a turbine engine

Jet exhaust noise reduction system and method

Aircraft wing/nacelle combination

Turbine section of high bypass turbofan

Exhaust duct for turbine forward of fan

Bypass duct heat exchanger with controlled fan

Intercooled cooling air with dual pass heat exchanger

Wide fuselage aircraft with increased boundary layer ingestion

Turbine section of high bypass turbofan

Transverse-mounted power turbine drive system

Aft fan counter-rotating turbine engine

Turbine engine with guide vanes forward of its fan blades

Cross flow fan with exit guide vanes

Heat exchanger for gas turbine engine

Pusher fan engine with in wing configuration

Double propulsor imbedded in aircraft tail with single core engine

Asymmetric fan nozzle in high-BPR separate-flow nacelle

Modifying a gas turbine engine to use a high pressure compressor as a low pressure compressor

System and method for controlling an environmental condition of an engine electronic component

Turbofan thrust reverser system

Reduced length transition ducts

Non-axisymmetric fixed or variable fan nozzle for boundary layer ingestion propulsion

RAYTHEON TECH CORP

Turbine section of high bypass turbofan

Turbine section of high bypass turbofan

Turbine section of high bypass turbofan

Turbine section of high bypass turbofan

Geared gas turbine engine with reduced fan noise

SUCIU GABRIEL L

Gas turbine engine driving multiple fans

Gas turbine engine with separate core and propulsion unit

ZYSMAN STEVEN H

Passive boundary layer bleed system for nacelle inlet airflow control

Passive boundary layer bleed system for nacelle inlet airflow control

ADAMS PAUL R

Turbine section of high bypass turbofan

Turbine section of high bypass turbofan

LORD WESLEY K

Transverse mounted gas turbine engine