Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
Type:
Grant
Filed:
August 21, 2018
Date of Patent:
March 17, 2020
Assignee:
CHROMALLOY GAS TURBINE LLC
Inventors:
David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, Daniel Folkers
Abstract: A turbine blade has an undercut beneath its platform proximate a trailing edge region. The undercut incorporates a curved portion to reduce to reduce undesirable stress concentration. The undercut shape includes a curved portion of decreasing radius with increasing distance from the underside of the platform.
Abstract: A method and apparatus for restoring displaced features on a turbine vane segment for a gas turbine engine, such as a vane segment in a low pressure turbine, and more specifically, the inner shroud thereof relative to the outer shroud thereof to meet the original design position and dimensions.
Type:
Grant
Filed:
March 13, 2014
Date of Patent:
September 22, 2015
Assignee:
CHROMALLOY GAS TURBINE LLC
Inventors:
Xuan Nguyen-Dinh, Roberto Flores Sandoval, Ben Blumanstock
Abstract: A tri-barrier ceramic coating system is provided having a base thermal barrier layer, an intermediate CMAS barrier layer, and a top erosion barrier layer, and the method of applying such a coating system to a substrate. The base layer has a typical columnar structure with inter-columnar gaps and intra-columnar micro-pores that provides the stress tolerance during thermal cycles. The intermediate CMAS barrier layer has the fiber-like columns with inter-columnar nano-pores and a grid structure on the bottom of the layer. The fine structured intermediate layer covers the gaps between the columns of the base layer and will block CMAS infiltration effectively. The top erosion resistant layer contains wider TBC columns with narrow inter-columnar gaps and a modified cauliflower-like TBC head that provides erosion resistance for the underlying layers. The tri-barrier coating microstructure will further reduce the thermal conductivity as comparing to the conventional single layer system.
Abstract: A method and apparatus for restoring displaced features on a turbine vane segment for a gas turbine engine, such as a vane segment in a low pressure turbine, and more specifically, the inner shroud thereof relative to the outer shroud thereof to meet the original design position and dimensions.
Type:
Application
Filed:
March 13, 2014
Publication date:
September 18, 2014
Applicant:
CHROMALLOY GAS TURBINE LLC
Inventors:
Xuan Nguyen-Dinh, Roberto Flores Sandoval, Ben Blumanstock
Abstract: A process for determining the position of closed holes in a component is provided. By carrying out laser triangulation measurements on an uncoated component and a coated component with holes, the exact position of the holes to be reopened may be detected following the coating. A device used to carry out this process is also provided.
Type:
Grant
Filed:
October 13, 2010
Date of Patent:
May 7, 2013
Assignees:
Siemens Aktiengesellschaft, Chromalloy Gas Turbine LLC
Inventors:
Georg Bostanjoglo, Torsten Melzer-Jokisch, Andreas Oppert, Dimitrios Thomaidis
Abstract: A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.
Type:
Grant
Filed:
February 17, 2009
Date of Patent:
June 8, 2010
Assignees:
Siemens Energy, Inc., Chromalloy Gas Turbine LLC
Inventors:
Martin C. Gosling, Jefferson Davis, Yong Kang
Abstract: A method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the method may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by heating the airfoil to no more than 750 degrees F. while applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. The load is up to 6000 lbf. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.
Type:
Grant
Filed:
November 2, 2006
Date of Patent:
May 26, 2009
Assignees:
Siemens Energy, Inc., Chromalloy Gas Turbine LLC
Inventors:
Jefferson Davis, Martin C. Gosling, Yong Kang