Rolls-royce Corporation

Anthony B Phipps

Adrian Lewis Harding

David Cameron Wright

Mark A Halliwell

Stephen Samuel Wiseall

Lynne H Turner

Sree Vamsi Tammineni

James William Cheang Meas

Nicholas S A Cristinacce

Paul H Edwards

James Meas

The ultrasonic inspectability of a supplied part out of which a final component is to be machined is determined by following a set of inspection rules for ultrasonic inspection of the supplied part. The rules determine which parts of the polygon cannot be inspected by a scan at a given ultrasound beam angle (typical beam angles are 0&#xb0;, +20&#xb0; and &#x2212;20&#xb0; relative to the perpendicular direction to the edge) along a given edge of the polygon.

Determination of ultrasonic inspectability

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. Alternatively a radially outer lobe of at least one of the rotor posts has reduced stiffness such that the load on the radially outer lobe of the at least one rotor post is shared with the other lobes of the at least one rotor post.

Turbomachine rotor blade and a turbomachine rotor

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.

Lead

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 structuresa bending moment is created about a baseformed in a test componentsuch that a bending moment forcecreates a bending moment in the test component. 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 componentrepresentative of a practical disc/blade combination is achieved.

Method and test component for rotatable disc parts

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.

Casing arrangement

An apparatus () for testing attachment features () of components () comprises a first member () having a first end (), a second end (), a first edge () and a second edge (). The first edge () has a first firtree slot () to receive a first component () and the second edge () has a second firtree slot () to receive a second component (). The first component () has a firtree attachment feature () to fit the first slot () and the second component () has a firtree attachment feature () to fit the second slot (). The first end () of the first member () has flanges () extending laterally and the second end () of the first member () has flanges () extending laterally such that the first member () is substantially H-shaped in cross-section. First load means () apply a load on the first component () and second load means () apply a load on the second component () substantially in the opposite direction to the load on the first component (). The apparatus may be used to test firtree attachments for turbine blades and discs.

Apparatus and a method for testing attachment features of components

The gate arrangementis provided in order to regulate coolant airflow in a path typically in a turbine bladeof a jet engine. The gate arrangementincludes a gate componenthaving an opening endwhich at low temperature is closed by a gate member. Due to different coefficients of expansion between the gate componentand the gate memberwhen the arrangementincreases in temperature there is a divergence between a seal endof the gate memberin order to open the opening endof the gate componentand to allow coolant airflow through the arrangement. Thus, coolant airflow is allowed for high temperatures but as the gate componentand gate memberconverge at sustained typically lower temperatures coolant airflow is stopped in order to prevent unnecessary cooling and so provide greater thermal efficiency.

Gate arrangement

A gas turbine engine turbine section includes a turbine disk () which carries a stage of turbine blades (). The turbine blades () have fir tree roots () which locate in fir tree grooves () in the rim of disk. Some of the projections that form the fir tree roots () of blades () and fir tree grooves () of disk () 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.

Method of and structure for enabling cooling of the engaging firtree features of a turbine disk and associated blades

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

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Uttoxeter, United Kingdom

Anthony B Phipps