Siemens Energy Global Gmbh & Co. Kg

Siemens Energy, Inc.

Blade Diagnostics Corporation

Siemens Aktiengesellschaft

Yuekun Zhou

Ching-Pang Lee

Steven Koester

Daniel M Eshak

Jerry Howard Griffin

Samuel R Miller, Jr

Heinrich Stüer

Daniel Vöhringer

Stefan Schmitt

Susanne Kamenzky

Adhlere Coffy

A bladed rotor system for a turbomachine includes a circumferential row of blades mounted on a rotor disc, and includes a plurality of under-platform dampers. Each damper is located between adjacent blade platforms. The plurality of dampers includes a first set of dampers and a second set of dampers. The dampers of the first set are distinguished from the dampers of the second set by a cross-sectional material distribution in the damper that is unique to the respective set. Dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.

Bladed rotor system and corresponding method of servicing

A bladed rotor system includes first and second sets of blades with respective airfoils each having at least one internal cavity. The airfoils of both the first and second sets of blades have identical outer shapes defined by an outer surface of an outer wall of the respective airfoils. The airfoils of the first set of blades are distinguished from the airfoils of the second set of blades by a geometry and/or position of at the least one internal cavity, which is unique to blades of a given set. The natural frequency of a blade of the first set differs from the natural frequency of a blade of the second set by a predetermined amount. The blades of the first set and the second set are alternately arranged in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.

Mistuning of turbine blades with one or more internal cavities

A bladed rotor system includes a circumferential row of blades mounted on a rotor disc. Each blade includes an airfoil and a shroud attached to the airfoil at a span-wise height of the airfoil. The row of blades includes a first set of blades and a second set of blades. The airfoils in the first and second set of blades have substantially identical cross-sectional geometry about a rotation axis. The blades of the second set are distinguished from the blades of the first set by a geometry of the shroud that is unique to the respective set, whereby the natural frequency of a blades in the first and second sets differ by a predetermined amount. Blades of the first set and the second set alternate in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.

Shrouded blades with improved flutter resistance

A turbine blade including a pressure sidewall () and a suction sidewall (), and at least one partition rib () extends between the pressure and suction sidewalls () to define a serpentine cooling path () having adjacent cooling channels () extending in the spanwise direction (S) within the airfoil (). A flow turning guide structure () extends around an end of the at least one partition rib () and includes a first element () extending from the pressure sidewall () to a lateral location in the cooling path between the pressure and suction sidewalls (), a second element () extending from the suction sidewall () to the lateral location in the cooling path between the pressure and suction sidewalls (). The first and second elements () include respective distal edges () that laterally overlap each other at the lateral location.

Turbine blade with a non-constraint flow turning guide structure

Growing community of inventors

Charlotte, NC, United States of America

Yuekun Zhou