SEAL FOR GIMBALING AND/OR FIXED ROCKET ENGINE NOZZLES, AND ASSOCIATED SYSTEMS AND METHODS

Aircraft propulsion system exhaust nozzle with ejector passage(s)

Exhaust collector conversion system and method

BRUSH SEAL COMPRISING A RUBBING-TOLERANT SUPPORT RING STRUCTURE

System and method for ram air intake for pulse combustors

Gas turbine engine with fluid circuit and ejector

SEAL FOR GIMBALING AND/OR FIXED ROCKET ENGINE NOZZLES, AND ASSOCIATED SYSTEMS AND METHODS

Convergent-divergent flap pair for a variable-geometry turbojet engine nozzle comprising cooling air circulation ducts connected through contact surfaces

Convergent-divergent flap pair for a variable-geometry turbojet engine nozzle, the flaps of which each comprise a cooling air circulation duct

NACELLE AIR INTAKE WITH AN ACOUSTIC PANEL

Exhaust collector conversion system and method

High bypass ratio engine bypass duct nozzle with controlled nozzle area

Exhaust nozzle of a gas turbine engine

System for controlling speed transition and thrust vectorisation in a multiple-shaped nozzle by secondary injection

DIFFUSER PIPE WITH SPLITTER VANE

HOT GAS PATH COMPONENT WITH METERING STRUCTURE INCLUDING CONVERGING-DIVERGING PASSAGE PORTIONS

THRUST NOZZLE FOR A TURBOFAN ENGINE ON A SUPERSONIC AIRCRAFT

Turbocharger and turbine housing therefor

Film-cooled multi-walled structure with one or more indentations

Wall of a hot gas component and hot gas component comprising a wall

Diffuser pipe with splitter vane

Turbine blade cooling system with channel transition

Convergent-divergent nozzle mechanism

Acoustic liners with oblique cellular structures

Nozzle of a turbomachine provided with chevrons with a non-axisymmetric inner face

Axial flow rotating machine and diffuser

Centrifugal compressor with diffuser with throat

Turbine blade cooling system with tip flag transition

Turbine blade cooling system with tip diffuser

Turbine blade cooling system with lower turning vane bank

Turbine blade cooling system with upper turning vane bank

Engine component with non-diffusing section

Engine component with non-diffusing section

FILM COOLING HOLE IN GAS TURBINE COMPONENTS

Gas turbine blade

Supply duct of a compressor of a turbine engine

Seal structure and turbine

System for discharging a compressor flow of a turbine engine

Compressor bleed apparatus for a turbine engine

Centrifugal compressor curved diffusing passage portion

Exhaust diffuser having ejection hole and suction hole, and gas turbine having the same

Generalized jet-effect and fluid-repellent corpus

CONVERGENT-DIVERGENT NOZZLE FOR A TURBOFAN ENGINE OF A SUPERSONIC AIRCRAFT AND METHOD FOR REDUCING THE BASE DRAG BEHIND SUCH NOZZLE

FILM HOLE ARRANGEMENT FOR A TURBINE ENGINE

Turbine blade with slot film cooling

Internally cooled engine components

Diffuser for a turbine engine and method of forming same

ARTICLE AND MANIFOLD FOR THERMAL ADJUSTMENT OF A TURBINE COMPONENT

Fan nacelle trailing edge

Fluid flow machine with high performance

Impingement insert for a gas turbine engine

Turbine component cooling holes

Labyrinth seal with lubricant directing projection

Internal cooling of stator vanes

Gas turbine engine trailing edge ejection holes

Variable thickness core for gas turbine engine component

Compressor

Apparatus and method for air particle separator in gas turbine engine

Article and manifold for thermal adjustment of a turbine component

Diffuser part for a gas turbine

Fan cooling hole array

Rotor blade having a flared tip

Convergent-divergent nozzle

Film cooled multi-walled structure with one or more indentations

Turbocharger diffuser center body

Airfoil showerhead pattern apparatus and system

Nozzle of a turbomachine provided with chevrons with a non-axisymmetric inner face

Gas turbine engine convergent/divergent nozzle with unitary synchronization ring for roller track nozzle

Axial flow rotating machine and diffuser

Exhaust liner flange cooling

Turbine outlet diffuser

Methods and apparatus for passive thrust vectoring and plume deflection

System and method for active clearance control

Cooled airfoil trailing edge and method of cooling the airfoil trailing edge

Methods and apparatus for passive thrust vectoring and plume deflection

Cooled turbine blade with double compound angled holes and slots

Passive boundary layer bleed system for nacelle inlet airflow control

Turbine blade

Cooling hole with crenellation features

Gas turbine engine components with lateral and forward sweep film cooling holes

Suction side turbine blade tip cooling

TURBOMACHINE EXHAUST DIFFUSER

Channeled spring seal for sealing an air gap between moving plates

Asymmetrically shaped trailing edge cooling holes

TURBINE AIRFOIL TRAILING EDGE BIFURCATED COOLING HOLES

Convective shielding cooling hole pattern

Trailing edge or tip flag antiflow separation

Multi-lobed cooling hole array

Cooling hole with crenellation features

Cooling hole with asymmetric diffuser

Airfoil

Airfoil

Exhaust gas diffuser for a gas turbine and a method for operating a gas turbine that comprises such an exhaust gas diffuser

System and method for integrating sections of a turbine

Boundary Layer Blowing Using Steam Seal Leakage Flow

ANGLED TRENCH DIFFUSER

Steam valve device and steam turbine plant

LEADING EDGE AIRFOIL-TO-PLATFORM FILLET COOLING TUBE

Cooled component wall in a turbine engine

Hub flowpath contour

Rotating machine with shaft sealing arrangement

Cooled conduit for conveying combustion gases

Component having a film cooling hole

Cooled aerofoil blade or vane

Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators

Fluid flow machine with blade row group

Cooling hole exits for a turbine bucket tip shroud

Propulsion system with canted multinozzle grid

Steam turbine stage

Flow-optimized bypass for turbo engines

Turbine arrangement and method of cooling a shroud located at the tip of a turbine blade

Centrifugal compressor forward thrust and turbine cooling apparatus

Turbine cooling air from a centrifugal compressor

Turbine airfoil cooling system with platform cooling channels with diffusion slots

Modular transvane assembly

Passive boundary layer bleed system for nacelle inlet airflow control

Diffuser for decelerating a compressed fluid

Performance improvements for pulse detonation engines

FILM COOLING OF TURBINE COMPONENTS

Divergent turbine nozzle

Rocket engine nozzle system

Steam valve and generator set

Component having a film cooling hole

Turbine component

Vectorable nozzle with pivotable triangular panels

Method and device for reducing engine noise

Augmentor pilot nozzle

Method of manufacturing a turbomachine component that includes cooling air discharge orifices

Nozzles with rotatable sections for variable thrust

Turbine airfoil cooling system with elbowed, diffusion film cooling hole

Yaw control device for a nozzle having a rectangular outlet section

Missile control system and method

Pulse combustion device

Gas turbine gas path contour

Gas turbine airfoil film cooling hole

Method and device for reducing engine noise

Variable geometry turbine

Axial divergent section slot nozzle

Method of achieving jet separation of an un-separated flow in a divergent nozzle body of a rocket engine

Supercharging air compressor for an internal combustion engine, internal combustion engine and method for that purpose

Seal for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods