Abstract: A neural network is trained for, and may be used in, the simulation of the fluid flow through a domain around an object geometry. A first training process for the neural network includes training (902) the network on a first set of encodings of pre-computed computational fluid dynamics (CFD) simulations for object geometries and associated boundary conditions. The first training process uses a first loss function that evaluates an error between the network output and the pre-computed CFD simulations. A second training process is then carried out which includes training (905) the network on a second set of encodings of object geometries and associated boundary conditions. The second training process uses a second loss function that evaluates an error between the network output and a set of fluid dynamics conditions.

Abstract: A turbomachine rotor includes a plurality of turbomachine rotor blades. The turbomachine rotor has a plurality of firtree shaped slots in its radially outer periphery to form a plurality of rotor posts. The turbomachine rotor blades have correspondingly shaped firtree roots to fit in the firtree shaped slots in the turbomachine rotor. The firtree roots of the turbomachine rotor blades comprise a plurality of radially spaced lobes on each of it flanks. The rotor posts of the turbomachine rotor comprise a plurality of radially spaced lobes on each of its flanks. A radially inner lobe of at least one of the turbomachine rotor blades has reduced stiffness such that the load on the radially inner lobe of the at least one turbomachine rotor blade is shared with the other lobes of the at least one turbomachine rotor blade.

Abstract: A lead for transmitting an electrical signal within a gas turbine engine, from a node at a first part of the gas turbine engine having a first surface to a second part of the gas turbine engine having a second surface, wherein the first part and the second part are coupled at a compressed joint, wherein the lead comprises: a node on the first surface of the first part; a first interconnect, adhered to the first surface of the first part; and a second interconnect, adhered to the second surface of the second part, wherein the first interconnect and the second interconnect abut at the compressed joint to provide, by their contact, a continuous electrical connection from the node to the second part.

Abstract: A lead for transmitting an electrical signal within a gas turbine engine, from a node at a first part of the gas turbine engine having a first surface to a second part of the gas turbine engine having a second surface, wherein the first part and the second part are coupled at a compressed joint, wherein the lead comprises: a node on the first surface of the first part; a first interconnect, adhered to the first surface of the first part; and a second interconnect, adhered to the second surface of the second part, wherein the first interconnect and the second interconnect abut at the compressed joint to provide, by their contact, a continuous electrical connection from the node to the second part.

Abstract: A lead for transmitting an electrical signal within a gas turbine engine, from a node at a first part of the gas turbine engine having a first surface to a second part of the gas turbine engine having a second surface, wherein the first part and the second part are coupled at a compressed joint, wherein the lead comprises: a node on the first surface of the first part; a first interconnect, adhered to the first surface of the first part; and a second interconnect, adhered to the second surface of the second part, wherein the first interconnect and the second interconnect abut at the compressed joint to provide, by their contact, a continuous electrical connection from the node to the second part.

Abstract: Rotatable discs combined with turbine blades in engines must be tested for critical life analysis. Thus, consideration must be made as to life expectancy for such components as a result of tensile circumferential hoops as generated by the weight of blades under rotation as well as compressive axial stress as a result of thermal gradients during initial warm up. Previous testing arrangements have considered tensile circumferential hoop stress but not compressive axial stress combinations such as “Von Mises” stress. By provision of bend structures 13, 223 a bending moment is created about a base 2, 22 formed in a test component 1, 21 such that a bending moment force 4, 24 creates a bending moment in the test component 1, 21. This bending moment results in a compressive axial stress reminiscent of that in a practical turbine engine disc as a result of initial thermal gradients. In such circumstances a more realistic testing of the component 1, 21 representative of a practical disc/blade combination is achieved.

Abstract: A turbomachine rotor includes a plurality of turbomachine rotor blades. The turbomachine rotor has a plurality of firtree shaped slots in its radially outer periphery to form a plurality of rotor posts. The turbomachine rotor blades have correspondingly shaped firtree roots to fit in the firtree shaped slots in the turbomachine rotor. The firtree roots of the turbomachine rotor blades comprise a plurality of radially spaced lobes on each of it flanks. The rotor posts of the turbomachine rotor comprise a plurality of radially spaced lobes on each of its flanks. A radially inner lobe of at least one of the turbomachine rotor blades has reduced stiffness such that the load on the radially inner lobe of the at least one turbomachine rotor blade is shared with the other lobes of the at least one turbomachine rotor blades.

Abstract: A casing arrangement of a gas turbine includes a casing member, which is formed to extend at least partially around the component. The casing member defines a fluid flow path for the flow of a cooling fluid therethrough.

Abstract: An apparatus (10) for testing attachment features (26,28,30,32) of components (12,14) comprises a first member (16) having a first end (18), a second end (20), a first edge (22) and a second edge (24). The first edge (22) has a first firtree slot (26) to receive a first component (12) and the second edge (24) has a second firtree slot (28) to receive a second component (14). The first component (12) has a firtree attachment feature (30) to fit the first slot (26) and the second component (14) has a firtree attachment feature (32) to fit the second slot (28). The first end (18) of the first member (16) has flanges (34,36) extending laterally and the second end (20) of the first member (16) has flanges (38,40) extending laterally such that the first member (16) is substantially H-shaped in cross-section.

Abstract: The gate arrangement 11 is provided in order to regulate coolant airflow in a path typically in a turbine blade 1 of a jet engine. The gate arrangement 11 includes a gate component 12 having an opening end 15 which at low temperature is closed by a gate member 14. Due to different coefficients of expansion between the gate component 12 and the gate member 14 when the arrangement 11 increases in temperature there is a divergence between a seal end 21 of the gate member 14 in order to open the opening end 15 of the gate component 12 and to allow coolant airflow through the arrangement 11. Thus, coolant airflow is allowed for high temperatures but as the gate component 12 and gate member 14 converge at sustained typically lower temperatures coolant airflow is stopped in order to prevent unnecessary cooling and so provide greater thermal efficiency.

Abstract: A gas turbine engine turbine section includes a turbine disk (20) which carries a stage of turbine blades (22). The turbine blades (22) have fir tree roots (24) which locate in fir tree grooves (26) in the rim of disk 20. Some of the projections that form the fir tree roots (24) of blades (22) and fir tree grooves (26) of disk (20) are truncated so as to define spaces between their truncated surfaces and the roots between adjacent overlapping projections, thus enabling the passing of a cooling air flow therethrough.

Abstract: A rotor drive (32) for a gas turbine engine (10) comprising a main drive body (44) having attachment lugs (46) on its radially outer port. The attachment lugs (46) are formed from a different material to the main drive body (44) and are bonded to the main drive body (44) by friction bonding.

Abstract: A lead for transmitting an electrical signal within a gas turbine engine, from a node at a first part of the gas turbine engine having a first surface to a second part of the gas turbine engine having a second surface, wherein the first part and the second part are coupled at a compressed joint, wherein the lead comprises: a node on the first surface of the first part; a first interconnect, adhered to the first surface of the first part; and a second interconnect, adhered to the second surface of the second part, wherein the first interconnect and the second interconnect abut at the compressed joint to provide, by their contact, a continuous electrical connection from the node to the second part.

Abstract: A gas turbine engine turbine section includes a turbine disk (20) which carries a stage of turbine blades (22). The turbine blades (22) have fir tree roots (24) which locate in fir tree grooves (26) in the rim of disk 20. Some of the projections that form the fir tree roots (24) of blades (22) and fir tree grooves (26) of disk (20) are truncated so as to define spaces between their truncated surfaces and the roots between adjacent overlapping projections, thus enabling the passing of a cooling air flow therethrough.

Abstract: A rotor drive (32) for a gas turbine engine (10) comprising a main drive body (44) having attachment lugs (46) on its radially outer port. The attachment lugs (46) are formed from a different material to the main drive body (44) and are bonded to the main drive body (44) by friction bonding.