Siemens Energy, Inc.

Siemens Aktiengesellschaft

Michael J Olejarski

David J Mitchell

Christopher J Muller

Derek A Bird

Rebecca L Kendall

Timothy E Mazzotta

Cristina C Popescu

Peter C Sullivan

Mihaela C Popescu

A thermocouple and a method for making the thermocouple. The thermocouple includes a thermocouple element shaft and at least one sleeve coupled to the thermocouple element shaft in at least one location of the thermocouple element shaft that is expected to experience wear.

Disc cavity thermocouple

A sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment.

Gas turbine sealing band arrangement having an underlap seal

System and methods for predicting a turbomachine engine safe start clearance following a shutdown of the turbomachine engine is provided. The system includes a controller operatively connected to a plurality of temperature detecting means (TDM). The TDMs are arranged at an upper and lower part of the engine casing, and are configured to sense parameters of the engine and to transmit the sensed parameters to the controller. The controller is configured to receive the sensed parameters and to determine, via a control application of the controller, whether components of the engine have sufficient clearance. The controller is further configured to transmit the clearance information, e.g., to a user. Based on the clearance information, the turbomachine engine is restarted.

Systems and methods for determining turbomachine engine safe start clearances following a shutdown of the turbomachine engine

A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap A sealing band is located in the opposing receiving slots to seal the annular gap Disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure The clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool To improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges.

Gas turbine including sealing band and anti-rotation device

A combustion turbine engine combustor igniter port alignment and dimensional verification tool is insertable in guide tube and igniter boss portions of the igniter port. The tool has concentrically nested outer and inner sleeves, having respective circumferential profiles that are separately slidably insertable within corresponding igniter port guide tube and igniter boss portions that have inner circumferential profiles in conformance with minimal dimension specifications. Concentric alignment of the guide tube and igniter boss is validated by inserting the nested outer and inner sleeves into the igniter port. The verification tool is capable of validating igniter port alignment and dimensions before the combustor is installed in a combustion turbine engine.

Combustion turbine engine combustor basket igniter port alignment verification tool and method for validating igniter alignment

A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.

Gas turbine including bellyband seal anti-rotation device

A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments.

Growing community of inventors

Merrit Island, FL, United States of America

Michael J Olejarski