Rolls-Royce Corporation

Christopher T J Sheaf

Zahid Muhammad Hussain

David G MacManus

Robert E Christie

Brian Handley

Fernando L Tejero Embuena

Richard Geoffrey Stretton

Andrew J Mullender

Chia Hui Lim

A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The nacelle further includes a protrusion extending radially inward from the air intake downstream of the intake lip. The protrusion extends circumferentially by a protrusion angle (&#x3b8;) with respect to the longitudinal centre line of the gas turbine engine.

Nacelle for gas turbine engine

A system and a method of designing a nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake, an internal surface, an azimuthal angle, and a plurality of intake lines. The air intake comprises, in flow series, an intake lip, a throat and a diffuser. The internal surface at least partially defines the air intake. The azimuthal angle is defined about the longitudinal centre line. The intake lines extend along the internal surface of the nacelle at respective values of the azimuthal angle. Each intake line axially defines the air intake along the longitudinal centre line at the respective value of the azimuthal angle. The internal surface of the nacelle between the plurality of intake lines at a given axial location along the longitudinal centre line is analytically defined by an equation.

Gas turbine engine nacelle and method of designing same

A gas turbine engine () for an aircraft comprises a pylon attachment () and a shaft () defining an engine centreline (). The engine centreline lies in an engine central plane () which intersects the pylon attachment. The gas turbine engine comprises an intake () having a non-axisymmetric geometry and a medial plane () defining left and right halves of the intake. The left and right halves are configured for at least one of optimum cross wind performance, optimum incidence performance and optimum cruise performance when the medial plane is aligned with a vertical plane. The intake is installed so that the medial plane is angularly offset with respect to the engine central plane. The engine may be installed on a wing of an aircraft with the medial plane closer to its optimal orientation than is the case for a conventional engine.

Gas turbine engine

A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The diffuser further includes a diffuser angle (&#x3b8;), indicating a degree of divergence of the diffuser relative to the longitudinal centre line. The diffuser angle (&#x3b8;) is from about 0 degrees to about 12 degrees.

A nacelle for housing a fan within a gas turbine engine having a longitudinal centre line includes a leading edge and a trailing edge. A nacelle length (L) is defined as an axial distance between the leading edge and the trailing edge. An azimuthal angle (&#x3b8;) is defined about the longitudinal centre line. The nacelle length (L) varies azimuthally. The nacelle length (L) decreases azimuthally from an inboard end of the nacelle to an outboard end of the nacelle.

Nacelle for gas turbine engine and aircraft comprising the same

A nacelle for a gas turbine engine having a longitudinal centre line includes an intake lip disposed at an upstream end of the nacelle. The intake lip includes a crown and a keel. The crown includes a crown leading edge and the keel includes a keel leading edge. The crown leading edge and the keel leading edge define a scarf line therebetween. The scarf line forms a scarf angle (&#x3b8;) relative to a reference line perpendicular to the longitudinal centre line. A fan casing is disposed downstream of the intake lip and includes a casing leading edge. The casing leading edge defines a droop line normal to the casing leading edge. The droop line forms a droop angle (&#x3b8;) relative to the longitudinal centre line. A relationship between the droop angle (&#x3b8;) and the scarf angle (&#x3b8;) is given by: &#x3b8;=&#x3b8;/1.5&#xb1;1 degree.

Nacelle for a gas turbine engine

A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

Fluid impingement arrangement

A boundary layer energizer () for energizing a boundary layer flow over a surface (), the boundary layer energizer () comprising a plurality of passages (), each passage terminating in a respective hole () provided on the surface (), the holes being arranged in a cluster () on the surface, wherein the plurality of passages are angled with respect to one another at the surface such that, when in use, a vortex () is formed by a fluid flowing through the plurality of passages.

Boundary layer energiser

A fluid transfer arrangement comprising a duct having a first end and a second end, a pulse generation mechanism located at the first end of the duct to direct fluid pulses towards the second end of the duct in use, and a baffle located at the second end of the duct that defines an aperture having sharp edges. The sharp edges generate ring vortex fluid flow from the aperture in use. Applications include impingement heating and cooling.

Fluid transfer arrangement

A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is at least one clean air outlet bounding the exhaust port and arranged to expel, in use, a vortical flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.

Breather duct shielding

A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.

A boundary layer energizer () for energizing a boundary layer flow () over a surface (), the boundary layer energizer () comprising one or more passages () terminating in one or more respective holes () provided on the surface (), wherein the one or more passages () comprises at least one fin () configured so as to generate a vortex flow in the one or more passages () such that, when in use, a fluid emanating from the one or more passages () flows in a vortex.

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Derby, United Kingdom

Christopher T J Sheaf