Siemens Energy, Inc.

Siemens Aktiengesellschaft

Zafir A M Abdo

Ahmed Kamel

Kazim Ozbaysal

Kevin Michael Light

Manish S Gurao

Anand A Kulkarni

Allister William James

Ovidiu Timotin

Thomas F Quinn

Derrick Marcantel

Diego L Caso, Jr

Jason E Williams

Navin J Manjooran

Anita Marie Hunt

A rotor disc configured to reduce the likelihood of fractures developing in spindle bolts in gas turbine engines is disclosed. The spindle bolts extend axially through the rotor disc to retain the rotor assembly in place in the gas turbine engine. The rotor disc may be formed from a rotor disc body having a plurality of circumferentially positioned spindle bolt holes sized to house a spindle bolts within each spindle bolt hole. One or more relief channels, which also may be referred to as scallops, may extend radially outward from one of the spindle bolt holes. The relief channels may foster removal of condensation and debris from the space between the spindle bolt and the surface forming the spindle bolt hole and may be configured to discourage the ingress of air through the relief channel and into space between the spindle bolt and the surface forming the spindle bolt hole.

Rotor disc with fluid removal channels to enhance life of spindle bolt

A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component.

Method for repairing a component for use in a turbine engine

A spindle bolt structure is provided in a gas turbine engine, and includes a pilot region located within a bolt hole extending through a seal disk. The pilot region includes a circumferential pilot ridge located adjacent to a downstream axial face of the seal disk and a circumferential trough portion located between a bolt shoulder and the pilot ridge. The trough portion defines a trough diameter that is less than a diameter of the bolt shoulder and less than a diameter of the pilot ridge. The bolt shoulder and pilot ridge are formed with an applied compressive residual stress and are positioned for engagement with the seal disk.

Gas turbine spindle bolt structure with reduced fretting fatigue

Ultrasonic bolt inspection apparatus and methods facilitate in situ as well as bench non-destructive evaluation (NDE) inspection of fastening bolt distal ends and their mating nuts. The apparatus is coupled to an exposed end of a fastener bolt head, its exposed thread tip or to a mating nut. The apparatus retains a phased array ultrasonic probe that generates inspection scan data and a rotational position encoder that generates rotational position data. The probe is coupled to an ultrasonic inspection system analyzer, which converts scan data into inspection data that characterizes possible defects in the inspected bolt. A system controller is coupled to the analyzer and the rotational position encoder, correlating rotation position data and inspection data, in order to identify location and characteristics of possible defects in the inspected bolt end.

Phased array ultrasonic bolt inspection apparatus and method

Ni base superalloys containing relatively large amounts of Al and/or Ti are known to be difficult to weld satisfactorily. As the Al and Ti content of the superalloy is increased to improve the strength, the weldability of the component is drastically reduced. It is concluded herein that reducing the &#x3b3;' phase improves weldability. A stepwise, controlled heating and cooling process is described to be used in cooperation with a welding process to reduce the &#x3b3;&#x2032; present and thereby improve weldability.

Hold and cool process for superalloy joining

A composition and method for cleaning turbine engine components () during servicing. An embodiment of the invention includes a colloidal mixture or slurry () of nanoparticles. The slurry may be nontoxic and provide optimal cleaning of tiny surface-exposed crevices () of braze joints and components. When a colloidal mixture is in a polar solvent, the pH of the slurry is maintained at about 5 to 9 and at the isoelectric point of the nanoparticles to minimize or prevent agglomeration. When a colloidal mixture is in a nonpolar solvent, the pH of the slurry is maintained at about 5 to 9 and at the isoelectric point of the nanoparticles to minimize or prevent agglomeration by use of surfactant additives.

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Orlando, FL, United States of America

Zafir A M Abdo