Rolls-royce Deutschland Ltd & Co. Kg

Rolls-royce Corporation

Rolls-royce Canada Limited

Harvard College

Villien, Benoit

Innes, Matthew, Christopher

Pham, Minh Quan

Shanian, Ali

Gerendas, Miklos

Guerrero, Fabian Enrique Sanchez

Scarinci, Thomas

Booth-morrison, Christopher

Schaenzer, Megan

Smith-roberge, Evelyne

Farhangi, Mehran

Miklos Gerendas

Sermed Sadig

Volker Herzog

Ali Shanian

Carl Carson

Thomas Doerr

Carsten Clemen

Karl Schreiber

Anthony Pidcock

Michael Ebel

Alan P Geary

Katia Bertoldi

Stefan Penz

Megan Schaenzer

Matthew Christopher Innes

Max Staufer

Minh Quan Pham

Farhad Javid

Christopher Booth-Morrison

Fabian Enrique Sanchez Guerrero

François-Xavier Jette

Maren Fanter

Evelyne Smith-Roberge

Kenneth James Young

Klaus Stefan Steinbach

Iain David Jeffrey Dupere

Michael Taylor

Thomas Scarinci

Ruud Eggels

Thomas Harold Gillespie

Benoit Villien

Geary Alan Philip

Klaus Stefan Steinbach Steinbach

Iain David Dupere Dupere

Kenneth James Young Young

Mehran Farhangi

Michael James Taylor

Carl J Carson

A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90&#xb0; before the measuring fluid exits the fluid channel at the at least one outlet.

Measuring device comprising at least one fluid channel for guiding a measurement fluid

A combustion chamber assembly for an engine includes a wall element fixed to a combustion chamber structure and a chamber between the wall element and the structure, the chamber being supplied with air through impingement-cooling openings in the structure and connected to the combustion space by film-cooling openings in the wall element. Two cooling-air holes formed in the structure generate a cooling-air flow toward the combustion space and past the wall element. The wall element has a flow guide device for generating at least one scavenging-air flow directed between the two cooling-air holes. A sum of flow cross sections of film-cooling openings in the wall element and of the flow guide device yields a larger area than a sum of flow cross sections of all wall element impingement-cooling openings via which air is guided through the structure into the chamber and to the rear side of the wall element.

Combustion chamber assembly with a flow guiding device comprising a wall element

The proposed solution relates to a combustion chamber assembly of an engine (T), in which an overrun of a spark plug is defined with a specific outer cone and a specific inner cone, and mixing air holes of a first arrangement and of at least one second arrangement that lie at least partially in a partial region of the overrun of the spark plug, said overrun being defined by the outer cone and the inner cone and extending downstream of the spark plug as far as an inner apex point (Si) of the inner cone, are formed with a flow cross section which is different from a flow cross section which the mixing air holes adjoining in the circumferential direction (U) of the respective arrangement have.

Combustion chamber assembly with adapted mixed air holes

Void structures, systems and devices with void structures, and methods of fabricating void structures are disclosed. A void structure is disclosed with a repeating elongated-aperture pattern designed to provide negative Poisson's Ratio behavior under macroscopic stress and strain loading. The pattern can include horizontal and vertical elliptically shaped apertures that are arranged on horizontal and vertical lines in a way that the lines are equally spaced in both dimensions. The centers of each aperture is on a crossing point of two of the lines. The vertical and horizontal elliptically shaped apertures alternate on the vertical and horizontal lines such that any vertical aperture is surrounded by horizontal apertures along the lines (and vice versa), and the next vertical apertures are found on both diagonals. The voids can also act as cooling and/or damping holes and, due to their arrangement, also as stress reduction features.

Void structures with repeating elongated-aperture pattern

A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is &#x2264;50&#xb0;.

Fuel spray nozzle comprising axially projecting air guiding element for a combustion chamber of a gas turbine engine

A wall of a structural component to be cooled by means of cooling air with at least one cooling air channel, which at least in its outflow area is arranged so as to be inclined at an angle with respect to the wall inclined, penetrating the wall from the side at which the cooling air is supplied to the thermally loaded side, characterized in that the cooling air channel has a tubular extension on the side where the cooling air is supplied, wherein the tubular extension is arranged at an angle to the surface of the wall and is supported by means of a rib with respect the surface of the wall, and in particular to an inner gas turbine combustion chamber wall with effusion holes.

Wall of a structural component, in particular of gas turbine combustion chamber wall, to be cooled by means of cooling air

A device for cooling a wall of a component of a gas turbine, where a flow passes parallel to the wall, having at least one inflow duct provided in the wall that issues into a recess of the wall for supplying cooling air, wherein a center axis of the inflow duct is aligned to an impact wall of double-convex design inside the recess.

Device for cooling a wall of a component of a gas turbine

The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile.

Gas-turbine combustion chamber with impingement-cooled bolts of the combustion chamber tiles

The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier.

Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes

An auxetic locking structure can be used as a mechanism for securing two or more members in an assembly or other system. The locking structure has void patterns on its exterior surface which permit the locking structure to reduce its outer diameter upon loading in an axial direction. Once the structure has been sufficiently loaded and the diameter has been sufficiently reduced, the locking structure may be positioned within a bore of an article, the axial load is then reduced, thus causing the locking structure to expand and engage the bore of the article. The locking structure and article are now secured to one another creating an improved assembly.

Auxetic locking pin

A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burnersdistributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.

Segmented combustion chamber head

A combustion chamber head of a gas turbine has a base plateprovided with a centric recessin which at least one burneris arranged, with the base platebeing connected to walls of the combustion chamberand to a burner sealsealing the burnertowards the rim of the recess. The burner sealis arranged upstream of the base plateand can be brought into contact with a collarprovided on the base plateand forming the rim of the centric recess. A holding elementof the burner sealis formed as a ring and arranged upstream of the burner sealand engages with at least one projectionof the base platein a tension-free state.

Combustion chamber head with holding means for seals on burners in gas turbines

A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wallto be cooled. The cooling-air supply device includes at least one air-supply ductwhich, in respect of its flow axis, is arranged vertically to the combustion chamber wall, with the air-supply ductbeing flow-connected to at least one cooling duct. The air-supply ductforms a throttle and has a smaller diameter than the cooling duct. The cooling ductissues at a shallow angle, relative to its flow axis, to the surface of the combustion chamber wallin a recessof the combustion chamber wall, with the cooling ductbeing designed to impart a swirl to the air flowing through it.

Gas-turbine combustion chamber with a cooling-air supply device

A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield (). A base plate () is arranged at a certain distance from the heat shield () and the base plate () is provided with several openings () in its rim area for passing the cooling air. Center axes () of the openings () are inclined at a shallow angle (&#x3b1;) relative to the combustion chamber wall ().

Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall

A combustion chamber head of a gas turbine has a confinement enclosing a dampening volume () and including a combustion chamber-opposite confinement () and a combustion chamber-side confinement (). The combustion chamber-side confinement () is provided as perforated wall (). In the edge area of the combustion chamber-side confinement (), cooling air can be routed onto the combustion chamber-side confinement () via recesses () in the confinement (). This cooling air, which flows along the combustion chamber-side confinement (), crosses the cooling air flow through the perforated wall () in the combustion chamber () without mixing with the latter, as both are separated by walls.

Combustion chamber head of a gas turbine

Growing community of inventors

Am Mellensee, Germany

Miklos Gerendas