Abstract: A method of modelling at least a part of a gas turbine engine, method including: determining whether a first match feature data entity, defining a first location where a first physical feature may associate with another physical feature of a data structure, and a second match feature data entity, defining a second location where the second physical feature may associate with another physical feature of the data structure, satisfy a first matching criterion, the data structure including: a first data entity representing a geometrical shape of the first physical feature, the first data entity being associated with the first match feature data entity; and a second data entity representing a geometrical shape of the second physical feature, the second data entity being associated with the second match feature data entity; and performing relative movement between the first physical feature and the second physical feature within a model using the determination.

Abstract: There is disclosed a component arranged to extend across a bypass duct (22) of a gas turbine engine (10), comprising: an outlet guide vane (24); and a structural support (26) arranged to structurally support a radially inner component of the gas turbine engine (10). The outlet guide vane (24) and the structural support (26) are contiguous at a merged portion (32) which is at a radially outer region of the component.

Abstract: A gas turbine engine includes a circumferential row of vanes directly upstream of an asymmetric gas flow path. At a given spanwise position, a tangential and axial position of the outer guide vanes varies along the circumferential row of vanes. One or more of the vanes are leant such that the tangential and axial position of one or more vanes of the circumferential row of vanes varies in a spanwise direction.

Abstract: A method of modelling at least a part of a gas turbine engine, the method comprising: generating a mesh for a feature using at least one data entity of a data structure, the at least one data entity defining a geometrical shape of the feature, wherein the data structure comprises: a set of data entities defining geometrical shapes of features; and modelling attributes associated with the geometrical shapes of the features; and assigning one or more modelling attributes using the modelling attributes associated with the geometrical shapes of the features.

Abstract: A method of manufacturing a gas turbine engine including designing a row of vanes provided upstream of an asymmetric gas flow volume. The method includes two dimensionally optimizing camberline and stagger angle of each vane, including using orthogonal polynomials to modify the camberline and stagger angle of each vane.

Abstract: An intake (12) for a gas turbine engine (10) has an annular lip structure (23) extending about a central axis (11) and defining an intake opening. The annular lip structure (23) has a leading edge (38) located between a radially inwardly facing portion of the intake and a radially outwardly facing portion of the intake (12). The annular lip structure (23) has upper, lower and opposing side regions on either side of the central axis (11). The annular lip structure (23) comprises a formation (40; 42; 48) on the radially inwardly facing portion arranged to create a non-symmetric flow field over the opposing side regions of the annular lip structure (23). The formation (40; 42; 48) may be actively controlled in response to ground vortex conditions.

Abstract: A computer implemented method of automatically designing a secondary air system for a gas turbine engine. The method comprises: receiving a geometry model of at least a part of a gas turbine engine, the geometry model including a plurality of data entities for a plurality of features of the gas turbine engine; defining a plurality of cavities using the plurality of data entities of the geometry model; determining a subset of cavities of the plurality of cavities that define at least a part of the secondary air system; and generating a secondary air system model from the determined subset of cavities that define at least a part of the second airflow system.

Abstract: A method of manufacturing a gas turbine engine including designing a row of vanes provided upstream of an asymmetric gas flow volume. The method includes two dimensionally optimising camberline and stagger angle of each vane, including using orthogonal polynomials to modify the camberline and stagger angle of each vane.

Abstract: A gas turbine engine comprising a circumferential row of vanes directly upstream of an asymmetric gas flow path. At a given spanwise position the tangential and axial position of the vanes varies along the row of vanes.

Abstract: A method of modelling at least a part of a gas turbine engine, the method comprising: generating a mesh for a feature using at least one data entity of a data structure, the at least one data entity defining a geometrical shape of the feature, wherein the data structure comprises: a set of data entities defining geometrical shapes of features; and modelling attributes associated with the geometrical shapes of the features; and assigning one or more modelling attributes using the modelling attributes associated with the geometrical shapes of the features.

Abstract: A method of modelling at least a part of a gas turbine engine, method including: determining whether a first match feature data entity, defining a first location where a first physical feature may associate with another physical feature of a data structure, and a second match feature data entity, defining a second location where the second physical feature may associate with another physical feature of the data structure, satisfy a first matching criterion, the data structure including: a first data entity representing a geometrical shape of the first physical feature, the first data entity being associated with the first match feature data entity; and a second data entity representing a geometrical shape of the second physical feature, the second data entity being associated with the second match feature data entity; and performing relative movement between the first physical feature and the second physical feature within a model using the determination.

Abstract: A method of modelling at least a part of a gas turbine engine, the method comprising: preparing a model of at least a part of the gas turbine engine using a data structure including: a first set of data entities representing geometrical shapes of physical features; and a second set of data entities representing geometrical shapes of aerodynamic boundaries, the second set of data entities being used to preserve aerodynamic design intent during preparation of the model.