United Technologies Corporation

Chromalloy Gas Turbine Corporation

Alstom Technology Limited

Other

Siemens Aktiengesellschaft

Power Systems Mfg., LLC

Power System Mfg., LLC

Power System Manufacturing, LLC

Charles A Ellis

David Medrano

Vincent C Martling

Zhenhua Xiao

Philip H McCluskey

Stephen Chin

J Page Strohl

Glenn A Cotnoir

David G Parker

George E Foster

Daniel R Godin

Richard Yu

H David Harter

Peter Tiemann

Peter Stuttaford

Robert James Bland

Harry E Eaton

Daniel E Kane

James Page Strohl

Adam Lee Hart

Harry Edwin Eaton, Jr

Kevin N McCusker

Daniel L Folkers

Gregory E Chetta

David M Nissley

Pedro Rivero

Kevin L Worley

W David Day

Terry Hollis

Mariano Medrano

David John Henriquez

Robert P Moore

John H Hughes

Michael McGhee

William D Neff

Susan A Rose

Joey C Hayes

Sherman Craig Creighton

Joseph A Oblak

Elliot I Goodman

Wesley Smith

Gerald Raresheid

James G Brackett

An apparatus and method for reducing the vibrations to a transition duct and improving the assembly and fit-up of a transition duct relative to a combustion system are disclosed. A damping member is provided between the transition duct and its mounting points to the gas turbine engine. The damping member comprises one or more layers of a composite material positioned between layers of sheet metal. An adjustable mounting system is also provided for the transition duct to allow for movement of a transition duct relative to the combustion liner.

Method and apparatus for mounting a transition duct in a gas turbine engine

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 +/&#x2212;0.049 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.

First stage turbine nozzle

A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, 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 an 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.

First stage turbine blade

A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.

Tunable transition duct side seals in a gas turbine engine

A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.

Compressor vane diaphragm

A system and method for reducing vibration and wear to adjacent platform surfaces and mounting locations of a vane segment in a gas turbine engine is disclosed. The present invention seeks to improve the interaction between mating faces of adjacent gas turbine vane assemblies by increasing the surface area where contact between the adjacent vanes occurs, so as to increase the damping capability and reduce the wear to the mating surfaces.

Stator damper shim

Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.

Hook ring segment for a compressor vane

A shroud for surrounding a portion of a turbine flow path having improved cooling and durability is disclosed. The shroud includes a plurality of generally axial cooling holes spaced a substantially equal distance apart and a plurality of generally circumferential cooling holes oriented generally perpendicular to the generally axial cooling holes. The generally circumferentially cooling holes are spaced a non-uniform distance apart so as to provide cooling to selected portions of shroud sidewalls to lower shroud operating temperatures and improve shroud durability.

Shroud block with enhanced cooling

A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.

Vane platform rail configuration for reduced airfoil stress

In gas turbines, compressed air is supplied via an air duct to combustion chambers and is heated there. Pressure losses in the air duct should be minimized in order to ensure good overall efficiency. This is achieved by the compressed air flowing with approximately constant velocity in the air duct from the compressor to the inlet into the combustion chamber. This is supported by the effective cross section of the air duct being almost constant over this distance.

Gas turbine with a compressor for air

Coatings containing at least 85% by volume crystalline mullite with less than 15% by volume of amorphous material and mullite dissociation phases are plasma sprayed onto the surface of a silicon based ceramic substrate by closely controlling the plasma spray parameters including the mullite feed stock and its particle size, the nozzle outlet stand-off distance, movement of the substrate past the plasma flow, back side heating of the substrate and the powder feed rate through the plasma spray gun.

Plasma sprayed mullite coatings on silicon based ceramic materials

A method of designing an outer air seal for the turbine blades of a gas turbine engine utilizes a knowledge-based product model software program for generating a parametric, three-dimensional, geometric model of the air seal. The product model software program is embodied in a knowledge-based engineering system. The model is created by the program through user selection of various structural feature options available for the air seal. The product model software program uses its internal knowledge base of configuration dependent parameter relationships and rules to design the model. Various types of analyses may then be run to validate the model. The model may be changed, if necessary, as a result of the analyses. The air seal model output from the product model software program is in a file format that defines the topology and dimensions of the geometry of the air seal. Other software programs may then use this product model output file in various ways, such as to re-generate the model for use in a CAD system.

Method of designing a turbine blade outer air seal

A turbine shroud segment includes a substrate and a coating layer having varying thickness. Various construction details are developed that provide minimal spalling of the coating layer during use of the shroud segment. In a particular embodiment, a shroud segment includes a coating layer that tapers towards the edges. The thickness tapers to a minimum thickness along the leading and trailing edges. Within the blade passing region of the shroud segment, the coating layer tapers towards the lateral edges to a thickness determined by the minimum thickness required for abrasive contact between the shroud segment and rotor blades. In another particular embodiment, the varying thickness of the coating layer is produced by forming the substrate with a concave surface, applying the coating, and subsequently machining back the coating layer to the desired dimensions.

Turbine shroud segment including a coating layer having varying thickness

Growing community of inventors

Stuart, FL, United States of America

Charles A Ellis