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US20150139787 TURBINE ENGINE STATOR WALL COVERED IN AN ABRADABLE COATING  
An annular turbine engine stator portion including a structural support provided in succession with a bonding underlayer and with an abradable coating formed by a resin filled with microbeads, the...
US20110243716 BLADE OUTER AIR SEAL WITH IMPROVED EFFICIENCY  
An air seal for use with rotating parts in a gas turbine engine has a matrix of agglomerated fine hBN (hexagonal boron nitride) powder, the particles of which having a first dimension, and of a...
US20120063888 ABRADABLE COATING WITH SAFETY FUSE  
An abradable coating for interaction with tips of airfoils (such as vanes or blades of a compressor of a gas turbine engine) includes a metal bond coat thermal, a ceramic layer, and an abradable...
US20130078085 BLADE AIR SEAL WITH INTEGRAL BARRIER  
An air seal for use with rotating parts includes a thermal barrier coating layer adhered to a substrate. An abradable layer is adhered to the thermal barrier coating layer. The abradable layer...
US20140093360 ALUMINUM BASED ABRADABLE MATERIAL WITH REDUCED METAL TRANSFER TO BLADES  
A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and...
US20150044035 HIGH POROSITY ABRADABLE COATING  
An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to...
US20120063881 ABRADABLE BUCKET SHROUD  
The present application provides an abradable bucket shroud for use with a bucket tip so as to limit a leakage flow therethrough and reduce heat loads thereon. The abradable bucket shroud may...
US20150118031 SYSTEM AND A METHOD OF INSTALLING A TIP SHROUD RING IN TURBINE DISKS  
The various embodiments of the present invention provide a method for installing a tip shroud on a turbine disk in a steam turbine. A tip shroud in the form of a ring is installed on the outer...
US20110182720 GAS TURBINE SHROUD WITH CERAMIC ABRADABLE COATINGS  
There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas...
US20130195633 GAS TURBINE ROTARY BLADE WITH TIP INSERT  
A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a...
US20110243715 ABRADABLE TURBINE AIR SEAL  
An abradable seal for a gas turbine engine includes a metal alloy and a plurality of pores in the metal alloy. The plurality of pores have a diameter of approximately 1 to 10 microns.
US20120107103 GAS TURBINE SHROUD WITH CERAMIC ABRADABLE LAYER  
A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an...
US20090097970 Systems and Methods Involving Abradable Air Seals  
Systems and methods involving air seals are provided. In this regard, a representative air seal for a gas turbine engine comprises a layer of ceramic exhibiting patterned surface features, wherein...
US20120189434 COATING WITH ABRADABILITY PROPORTIONAL TO INTERACTION RATE  
A seal in a gas turbine engine component between an airfoil with a radial outward end and a seal member adjacent it coated with an abrasive layer having a ceramic component in a matrix of a metal...
US20130071234 ABRADABLE PANEL AND METHOD OF FORMING THE SAME  
An abradable panel for a fan track liner assembly comprises an abradable layer comprising a syntactic material. The abradable panel is arranged to be attached to a fan track liner so as to provide...
US20110286839 FAN CASE WITH RUB ELEMENTS  
A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer...
US20090110547 Method for producing a contoured gap, and turbo-engine comprising contoured gap  
A method for producing a contoured gap between a rotor and a stator of a turbo-engine is provided. A first turbo-engine drives a second turbo-engine by means of a common shaft, the shaft being...
US20140356142 Gas Turbine with Honeycomb Seal  
Provided is a gas turbine that can solve a problem in which a seal fin of a turbine blade is abraded by a brazed place of a honeycomb seal. A gas turbine 100 includes a compressor 10, a combustor...
US20130236298 SEALING ASSEMBLY FOR USE IN A ROTARY MACHINE AND METHODS FOR ASSEMBLING A ROTARY MACHINE  
A sealing assembly for use with a rotary machine is described herein. The sealing assembly includes a stator shroud coupled to the casing. The stator shroud includes an inner surface that at least...
US20140064938 RUB TOLERANT FAN CASE  
A case apparatus for a gas turbine engine includes an annular case having an interior surface with annular recess formed therein; and an annular bumper disposed in the recess, the bumper...
US20140321969 SLIDE RING SEAL  
A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall...
US20050129511 Turbine blade tip with optimized abrasive  
A new abrasive blade tip treatment is disclosed with the potential to provide improved blade tip clearance control in the turbine section of modern industrial gas turbines (IGT's). This blade tip...
US20140227088 ASSEMBLY FORMED BY A TURBINE NOZZLE OR A COMPRESSOR DIFFUSER MADE OF CMC FOR A TURBINE ENGINE AND BY AN ABRADABLE MATERIAL SUPPORT RING, AND A TURBINE OR A COMPRESSOR INCORPORATING SUCH AN ASSEMBLY  
A turbine nozzle or a compressor diffuser includes sectors made of CMC material, each having an inner platform, an outer platform, and airfoils. An abradable material support ring is made up of...
US20090110548 ABRADABLE RIM SEAL FOR LOW PRESSURE TURBINE STAGE  
An abradable rim seal arrangement for a turbine stage of a gas turbine engine, which includes an abradable rim seat attached to a leading edge of an annular inner duct of a turbine exhaust case,...
US20130017070 TURBINE SEAL, TURBINE, AND PROCESS OF FABRICATING A TURBINE SEAL  
Provided is a turbine seal, a turbine, and a process of fabricating a turbine seal. The turbine seal includes a metallic foam positioned along a hot gas path of a turbine. The turbine includes a...
US20080279678 Abradable CMC stacked laminate ring segment for a gas turbine  
A pattern of depressions (36) in a sealing surface (34) on a CMC wall (32) of gas turbine ring segment (30) allows minimum clearance against turbine blades tips, and thus maximizes working gas...
US20100074731 Gas Turbine Sealing Apparatus  
A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing...
US20150240651 TURBINE ABRADABLE LAYER WITH PROGRESSIVE WEAR ZONE MULTI LEVEL RIDGE ARRAYS  
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting alternating rows of first and second height ridges in planform...
US20130323034 ROTARY MACHINE  
In a compressor (11) of a turbocharger (1), a compressor wheel (14) is provided in a housing (12) to be capable of rotating. When the wheel (14) rotates, air suctioned through an inlet of the...
US20090110536 Blade outer air seal with improved thermomechanical fatigue life  
A blade outer air seal for a gas turbine has an abradable coating with a substantially uniform thickness during service use. Prior to being placed in service, the abradable coating has a central...
US20060213435 Inlet coating for gas turbines  
An abradable coating for gas turbines is provided. The abradable coating is used for sealing a radial gap between a casing (11) of the gas turbine and rotating blades (10) of the same. The...
US20070248457 RUB COATING FOR GAS TURBINE ENGINE COMPRESSORS  
Rub coatings, and methods for applying rub coatings, are provided for compressor assemblies of gas turbine engine assemblies. The coating may be applied as an initial coating to a new surface of a...
US20080292452 Housing for a Supercharger Assembly  
A housing for a supercharger assembly is provided having an inner wall at least partially defining a rotor cavity. A layer is formed from a sacrificial polymeric material and is provided on at...
US20080273967 Ring seal for a turbine engine  
A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a...
US20080219835 ABRADABLE COMPONENT FOR A GAS TURBINE ENGINE  
A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the...
US20120177484 Elliptical Sealing System  
The present application provides an elliptical sealing system for use with a rotor and a stator housing of a rotary machine. The elliptical sealing system may include a number of sealing segments...
US20120099970 FRIABLE CERAMIC ROTOR SHAFT ABRASIVE COATING  
An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer...
US20090022583 Turbine blade with a cover plate and a protective layer applied to the cover plate  
The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of...
US20080199301 Fan Case Reinforcement in a Gas Turbine Jet Engine  
Described is reinforcement of a fan case in a gas turbine jet engine. In one embodiment, a containment ring and a heat resistance ring are shrink interference fit on the inside diameter of the fan...
US20110299977 PATCH RING SEGMENT FOR A TURBOMACHINE COMPRESSOR  
A turbomachine includes a compressor provided with a casing having an inner surface defining a flow path. At least one blade is rotatable within the flow path. The at least one blade includes a...
US20150176424 SEAL SYSTEM FOR A GAS TURBINE  
The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first...
US20090196730 Gas turbine with a compressor with self-healing abradable coating  
A gas turbine with a compressor includes at least one row of blades, with the blades having a free end each, with a self-healing abradable coating being provided adjacent to the free end of the...
US20140321993 ELLIPTICAL SEALING SYSTEM  
Some embodiments of the invention are directed to an elliptical sealing system for use with a rotor and a stator housing of a rotary machine. The elliptical sealing system includes a plurality of...
US20140271148 ENGINE CASING ASSEMBLY  
A gas turbine engine casing assembly has a first casing element which is located radially outward of one or more rotating aerofoil elements of the gas turbine engine. The first casing element is...
US20150240653 TURBINE ABRADABLE LAYER WITH ZIG ZAG GROOVE PATTERN  
Turbine and compressor casing abradable component embodiments for turbine engines, with zig-zag pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and...
US20150198056 ABRADABLE SEAL HAVING NANOLAYER MATERIAL  
A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon. An abradable seal circumscribes the blades and includes a polymeric...
US20150240652 TURBINE ABRADABLE LAYER WITH ASYMMETRIC RIDGES OR GROOVES  
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section...
US20150093237 CERAMIC MATRIX COMPOSITE COMPONENT, TURBINE SYSTEM AND FABRICATION PROCESS  
A ceramic matrix composite component, turbine system and fabrication process are disclosed. The ceramic matrix composite (CMC) component includes a CMC material, an environmental barrier coating...
US20080260523 GAS TURBINE ENGINE WITH INTEGRATED ABRADABLE SEAL  
An abradable land assembly for a gas turbine engine includes a mount portion and an open cell portion which is to be abraded. Both portions are formed integrally from a single piece of material.
US20080175706 STEAM TURBINE  
A steam turbine has: a casing; a rotor rotatably arranged in the casing; a nozzle diaphragm concentrically arranged with respect to the rotor, the nozzle diaphragm being engaged with the casing;...

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