Siemens Power Generation, Inc.

Siemens Energy, Inc.

Siemens Westinghouse Power Corporation

Siemens Power Corporation, Inc.

Mitsubishi Hitachi Power Systems Americas, Inc.

Mitsubishi Power Systems Americas, Inc.

Chad Garner

Santo F Scimeca

Barton M Pepperman

An inter stage seal housing for a turbine engine having upper and lower half inter stage seal housings in which a contact sealing surface of the seal housing is restored after an interval of engine operation. The contact sealing surface is restored by fitting a replaceable wear strip on the downstream sealing surface of the seal housing. In order to fit the replaceable wear strip, a circumferential groove is machined along an outer peripheral edge of the seal housing. The groove is machined to include axial location and radial retention such that the wear strips can be slid into the upper half and lower half inter stage seal housing circumferentially from the horizontal joint. The groove includes through holes and the wear strips include corresponding threaded holes such that the wear strips can be fastened in the groove by fasteners and fastener retention hardware.

Inter stage seal housing having a replaceable wear strip

A turbine airfoil support system for supporting a turbine blade to prevent wear during turning gear operation when a rotor assembly supporting the turbine blade rotates at about two revolutions per minute (RPM) to keep the turbine ready for quick startup requirements. The turbine airfoil support system may be formed from a radial biasing spring positioned between a radially outermost point of a disk steeple extending from a rotor assembly and a radially inner surface of the platform. The radial biasing spring may be formed from a first flat member with a disk steeple engaging surface, a second flat member with a blade platform engaging surface, a bent biasing section extending from the first flat member to the second flat member and biasing the first and second flat members away from each other, and a stress reducing member extending from the second flat member toward the first flat member.

Wear prevention spring for turbine blade

A blade assembly () for a turbine () including a vibration damper () having a mounting base () sealingly disposed at an inlet end () of a cooling fluid passageway () within the root section () of the blade assembly and including an opening () in the mounting base for passing cooling fluid into the cooling passageway. The opening is sized to function effectively as an orifice for limiting a maximum flow rate of cooling fluid in the event of a breach of the cooling fluid passageway downstream of the inlet end. A wear feature () is formed on the distal end of the vibration damper opposed the mounting base for rubbing interface with a complementary wear feature attached to a wall () of the cooling fluid passageway. The wear feature may include a non-planar wear surface such as angularly disposed wear surfaces () effective to resist vibrational movement in two directions.

Turbine blade with vibration damper

Embodiments of the invention relate to an axial locking system for a row of blades in a turbine engine. While achieving the desired axial restraint, the system is configured to allow remote manipulation of the locking system. For example, a locking system provided on the upstream side of a row of blades can be accessed from the downstream side of the blades. Such a system can provide significant cost savings during the installation and removal of the blades. In one embodiment, the axial locking system can include a plate with a rotatable cam. Cooperating with the disc, the cam can be rotated to bring the radially outer end of the plate into locking engagement with the turbine blades. The cam can be manipulated from the other side of the disc by a tool extending through a passage formed between the disc and the blade root.

Remotely accessible locking system for turbine blades

Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of the compressor. In one embodiment, a substantially annular seal land is secured at one end to an annular extension arm on a compressor disk. When the engine reaches steady state operation, the non-attached end of the seal land can extend radially outward to reduce the clearance between the seal land and a shroud extending over the ends of the adjacent stationary airfoils. The seal land can be designed to resist the rotational forces imparted by the turning rotor until a certain desired operating condition is reached. In one embodiment, the seal land reaches full extension when the engine is operating at about 3600 rpm.

Compressor system with movable seal lands

Aspects of the invention relate to a compressor system for a turbine engine that not only allows for larger compressor blade tip clearances as the engine passes through non-standard operating conditions, but also minimizes clearances during normal engine operation, thereby increasing efficiency of the compressor. The blade assembly can include an airfoil having a movable tip insert recessed within a pocket in the radially distal end of the airfoil. The tip insert can move radially outward from a predetermined recessed position to a predetermined extended position. An abutment surface can be provided within the pocket for engaging the tip insert and/or other associated components so as to limit the extension of the tip insert to the predetermined extended position such that the tip insert does not impinge on the stationary compressor structure and such that a spring operatively associated with the tip insert does not overextend its operational limits.

Growing community of inventors

Orlando, FL, United States of America

Chad Garner