Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Siemens Power Generation, Inc.

Phillip W Gravett

Yevgeniy P Shteyman

William Richard Ryan

Christopher W Ross

Nancy H Ulerich

Kai Kadau

Christian Amann

Sachin R Shinde

Richard D Holm

Stephen Williamson

Thomas J Gordon

Lawrence Lee Ross

Brian D Ottinger

Nicholas D'Amico

Santosh Narasimhachary

A turbine blade includes a platform, a blade airfoil attached to one side of the platform, a blade root attached to the other side of the platform, a manifold attached to the blade root. The blade root defines a first cooling passage and a second cooling passage. The manifold includes an outer wall, a first compartment having a first flow area defined by a first aperture formed at the outer wall, and a second compartment having a second flow area defined by a second aperture formed at the outer wall. The first compartment meters a non-zero first flow of cooling air to the first cooling passage through the first flow area. The second compartment meters a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area.

Manifold for turbine blade of gas turbine engine

A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a first mating surface. The sealing band arrangement further includes a block having a locking section located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks. A tapered pin element extends through the seal strip segment and the block. The tapered pin element is friction welded to both the seal strip segment and the block to attach the block to the first mating surface of the seal strip segment.

Gas turbine rotor sealing band arrangement having a friction welded pin element

A probabilistic estimation of fatigue crack life of a component is provided. A plurality of representations of the component is defined from material property scatter data and flaw-size scatter data, wherein each representation is defined by one possible material condition and flaw-size condition associated with the component. For each representation, a component location is selected and a determination is made whether said individual representation fails after a given number of cycles N, based on the calculation of a crack growth in the selected location. The crack growth is calculated on the basis of the material condition and the flaw-size condition in the selected location. Failure of the individual representation is determined if the crack growth is determined to be unstable. The sum total of the number of the representations that failed after N cycles is determined. A probability of failure of the component after N cycles is then determined.

Method and system for probabilistic fatigue crack life estimation

Aspects of the invention related to a system for providing advance notice of impending contact between a stationary component and a rotating component in a turbine engine. For example, the system can be used to warn of potential contact between a seal holder and a rotor disk in the compressor section of the engine. In one embodiment, a pad or other component can be provided on the stationary seal holder. If the seal holder and the rotor disk approach each other during operation, the pad can contact the rotor disk prior to actual contact between the seal holder and the rotor disk. An optical and/or an acoustic signal can be generated by such contact. The signals can be detected remotely from the point of contact by a signal detection device, thereby avoiding the need to pass wires through the compressor section.

Warning system for turbine component contact

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Orlando, FL, United States of America

Phillip W Gravett