Rolls-royce Deutschland Ltd & Co. Kg

Marco Rose

Rene Spieweg

Fredi Holste

Dimitrie Negulescu

Alastair D Moore

Christoph Richter

Christian Mundt

Carlos Omar Marquez Gutierrez

Lars Willer

Frank Arnold

Gregory Mack

Jürgen Dierke

James Robert Mcleavy Hill

An engine pod for a gas turbine engine which includes a pod wall having an inside and an outside. The pod wall includes a fixed downstream portion and a displaceable upstream portion which is displaceable in the axial direction between a first upstream position and a second downstream position. At its downstream end facing the fixed portion, the upstream portion forms a radially outer rear edge and axially spaced therefrom a radially inner rear edge, with a recess in between. It is provided that adjacent to the recess, an air-permeable structure is formed in the upstream portion which is intended and configured, in the first upstream position of the displaceable portion, to conduct air flowing in the region of the recess to the inside of the displaceable portion. According to a further aspect of the invention, the axial position of the radially inner rear edge varies in the circumferential direction.

Engine nacelle for a gas turbine engine

The present invention relates to a nozzle with a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements, with the first azimuthal guide wall forming a first trailing edge and two first edges to the wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements, with the second azimuthal guide wail forming a second trailing edge and two second edges to the wall elements. A wall element connects a first guiding device and a second guiding device. The wall elements have a curved course in the axial direction.

Nozzle with guiding devices

A turbomachine has an annular main flow duct through which passes a flow, and in which is arranged at least one stator provided with stator vanes. The stator vanes each have at least one recess issuing into a flow duct inside the stator vanes and the flow duct issues into a bypass duct of the turbomachine via at least one outflow duct provided with a shut-off element.

Noise-reduced turbomachine

A nozzle has a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements. A wall element connects a first guiding device and a second guiding device. At least some of the first azimuthal guide walls of the first guiding device and at least some of the second azimuthal guide walls of the second guiding device have differing axial lengths, so that first and second trailing edges thereof have differing axial positions.

A nozzle includes first guiding elements () circumferentially arranged at a nozzle rim (). To reduce sound emission while keeping flow losses low, second guiding elements () are also circumferentially arranged at the nozzle rim (), with one of the first and second guiding elements () being diffuser-type and the other of the first and second guiding elements () being nozzle-type and with both types of guiding elements circumferentially alternating with each other.

Nozzle with guiding elements

A device for simulating sound produced by certain equipment, for example a rotor-stator arrangement of a turbomachine, or for generation of opposing sound fields for active sound control, including active sound reduction and active sound amplification, comprises flow obstacles () provided in a flow duct () flown by a fluid at which vortices () are shed at a certain frequency depending on the shape and size of the flow obstacles and the velocity of flow. The quantity and spatial arrangement of the flow obstacles is selected such that a periodically spatially and temporally changing pressure field for the excitation of a sound field () of a certain modal content is produced by the entirety of the vortices shed. This sound field reacts synchronizingly on the vortex shedding. The resonant circuit so formed, whose vortex shedding frequency is in the range of the resonant frequency of the sound field to be excited, is the sound source.

Arrangement for the generation of sonic fields of a specific modal composition

A turboprop aircraft engine includes at least one outer air intake and at least one downstream inner duct system for the delivery of air to a compressor, and the inner duct system spirals around the center axis of the engine.

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Freiberg, Germany

Marco Rose