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| Number | Title | Issue Date |
| 8161753 | Brazed joint between a titanium-based metal part and a ceramic part based on silicon carbide (SIC) and/or carbon An assembly including a stack structure made up of the following elements assembled together by brazing: the titanium-based metal piece; a first intermediate piece suitable for deforming to accommodate differential expansion between the metal piece and a piece made ... | 04/24/2012 |
| 8141364 | Brazed joint between a metal part and a ceramic part An assembly including a metal piece, a piece made of ceramic material, and at least one intermediate connection element assembled to each of the pieces by brazing. The intermediate connection element includes a deformable sheet presenting at least two flat zones bra... | 03/27/2012 |
| 8074453 | Combustion chamber lining A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2 each have a straight hollow tubular profi... | 12/13/2011 |
| 8069670 | Combustion chamber wall A combustion chamber wall in a combustion chamber is proposed, The chamber wall has a support structure with a number of heat shield which are attached to the support structure with the aid of a fastening unit. The fastening unit encompasses a spring device which is... | 12/06/2011 |
| 7950234 | Ceramic matrix composite turbine engine components with unitary stiffening frame Aspects of the invention are directed to a ring seal segment having a base portion and a frame portion. The base portion and the frame portion are a unitary structure. The frame portion is made of four unitary side walls: a forward wall, an aft wall and a pair of tr... | 05/31/2011 |
| 7908867 | Wavy CMC wall hybrid ceramic apparatus A ceramic hybrid structure (207, 502, 602, 608) that includes a wavy ceramic matrix composite (CMC) wall (214, 532, 603, 609) bonded with a ceramic insulating layer (230, 538, 604, 610) having a distal surface (242) that may define a hot ... | 03/22/2011 |
| 7805945 | Thermal shield, especially for lining the wall of a combustion chamber A highly durable, high-strength thermal shield element is provided for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal shield element comprises a base produced from a solidified cast ceramic material into which a plurali... | 10/05/2010 |
| 7788928 | Annular combustion chamber of a turbomachine Annular combustion chamber of a turbomachine is provided. The combustion chamber includes an inner wall, an outer wall, a chamber bottom disposed between the walls in the upstream region of the chamber, and two attachment flanges disposed downstream of the chamber b... | 09/07/2010 |
| 7762076 | Attachment of a ceramic combustor can A combustor assembly includes a metal section having an axial slot that receives a ceramic section. A clamp is received about the axial slot to secure the metal section and ceramic section together. Tabs on the metal section, a gasket between the metal section and t... | 07/27/2010 |
| 7665307 | Dual wall combustor liner A combustor liner assembly includes an outer shell made of a ceramic composite and an inner heat shell that is supported within the outer shell. The inner heat shield defines a surface that is exposed to combustion gases. The inner heat shield is made of material th... | 02/23/2010 |
| 7360364 | Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled toge... | 04/22/2008 |
| 7311175 | Acoustic liner with bypass cooling An acoustic liner 20 includes a remote panel 26, a proximate panel 28 transversely spaced from the remote panel and a resonator chamber 34b residing between the panels. Perforations 38 penetrate the proximate panel in regist... | 12/25/2007 |
| 7311790 | Hybrid structure using ceramic tiles and method of manufacture A hybrid structure (50) and method of manufacturing the same including a structural ceramic matrix composite (CMC) material (42) coated with a layer of ceramic insulating tiles (24). Individual ceramic tiles are attached to a surface (22)... | 12/25/2007 |
| 7299622 | Component for being subjected to high thermal load during operation and a method for manufacturing such a component Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) tha... | 11/27/2007 |
| 7279438 | Coated insulation board or batt An insulation composite for attenuating energy or sound transmission has a body layer of insulating material with a roughly textured face and a uniform thickness solid cover layer permanently embedded in the body layer to a partial depth so that material of the body... | 10/09/2007 |
| 7263772 | Foam wall combustor construction A method of manufacturing a composite wall with an open cell metal foam core layer bonded to an inner cladding layer and an outer cladding layer. The method involves: creating a core substrate of open cell gas permeable foam in a chosen shape; impregnating the open ... | 09/04/2007 |
| 7249462 | Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils... | 07/31/2007 |
| 7237388 | Assembly comprising a gas turbine combustion chamber integrated with a high pressure turbine nozzle The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine nozzle assembly to inner and outer metal shrouds in order to hold said... | 07/03/2007 |
| 7237389 | Attachment system for ceramic combustor liner Aspects of the invention relate to a system for attaching a ceramic liner to a non-ceramic combustor head-end component while accommodating different rates of thermal expansion of these components. One end of the liner can be received within a slot formed by the com... | 07/03/2007 |
| 7234306 | Gas turbine combustion chamber made of CMC and supported in a metal casing by CMC linking members The annular combustion chamber having ceramic matrix composite material walls is mounted inside a metal casing by linking members fastened to the chamber by brazing. The linking members comprise a plurality of inner linking tabs and a plurality of outer linking tabs... | 06/26/2007 |
| 7208230 | Optical reflector for reducing radiation heat transfer to hot engine parts A high temperature gas turbine component for use in the gas flow path that comprises a specular optical reflector coating system. A thin specular optical reflector coating system is applied to the gas flow path of the component, that is, the surface of the component... | 04/24/2007 |
| 7198860 | Ceramic tile insulation for gas turbine component Ceramic tile (32) insulation for protecting a substrate material (34) in a high temperature environment. A plurality of ceramic tiles (78) may be used in combination with a monolithic layer of ceramic insulation (80) to protect a fillet r... | 04/03/2007 |
| 7191665 | Support for a reflective target A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating te... | 03/20/2007 |
| 7186091 | Methods and apparatus for cooling gas turbine engine components A method of cooling a gas turbine engine component having a perforate metal wall includes providing a plurality of pores in the wall, wherein the pores extend substantially perpendicularly through the wall, and wherein the pores are covered and sealed closed at firs... | 03/06/2007 |
| 7121096 | Gas turbine engine combustor A combustor for a gas turbine engine comprising a combustion chamber wall having formed therein at least one hole for admitting air into the combustion chamber and at least one air intake chute aligned with said hole. The air intake chutes are attached to the combus... | 10/17/2006 |
| 7117676 | Apparatus for mixing fluids A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the abse... | 10/10/2006 |
| 7104067 | Combustor liner with inverted turbulators A combustor liner for a gas turbine, the combustor liner having a substantially cylindrical shape; and a plurality of axially spaced circumferential grooves formed in an outside surface of the combustor liner. ... | 09/12/2006 |
| 7089742 | Wall elements for gas turbine engine combustors A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality... | 08/15/2006 |
| 7076956 | Combustion chamber for gas turbine engine A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a damping tube in flow communication with the chamber interior. The damping tube is provided with at least one cooling hole extendi... | 07/18/2006 |
| 7065971 | Device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas ... | 06/27/2006 |
| 7059133 | Dilution air hole in a gas turbine combustion chamber with combustion chamber tiles A gas turbine combustion chamber includes combustion chamber tiles 3 attached to a supporting structure 6 of the gas turbine combustion chamber, with each tile possessing at least one dilution air hole 4 which is flush with a dilution air hole o... | 06/13/2006 |
| 7047722 | Small scale hybrid engine (SSHE) utilizing fossil fuels This invention describes a miniaturized hybrid diesel-electric engine formed by a closed-loop system powered by plasma-aided combustion of JP-8 fuel (or other hydrocarbon fuels) working in tandem with a vapor cycle utilizing miniaturized expanders and condensers. Th... | 05/23/2006 |
| 7017350 | Combustion chamber having a flexible connection between a chamber end wall and a chamber side wall The invention relates to an annular combustion chamber for a turbomachine of axis X, in which the chamber end wall is fixed to inner and outer side walls by means of a plurality of radially-inner attachment fittings and by means of a plurality of radially-outer atta... | 03/28/2006 |
| 7007480 | Multi-axial pivoting combustor liner in gas turbine engine A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and r... | 03/07/2006 |
| 7007481 | Thick coated combustor liner A combustor liner includes panels joined together at a cooling nugget including a bridge and a lip extending therefrom. The lip defines a slot terminating in an outlet. Thermal barrier coating covers inboard surfaces of the panels and lip with a nominal thickness. T... | 03/07/2006 |
| 7007486 | Apparatus and method for selecting a flow mixture A counter-flow system for use in a turbine for selecting various mixtures of fluids for use with the system. The system may be used for a combustor for a gas powered turbine which employs a heat exchanger to combust a fuel without the emission of undesired chemical ... | 03/07/2006 |
| 7003959 | High temperature splash plate for temperature reduction by optical reflection and process for manufacturing A high temperature splash plate for use in the combustor of a gas turbine engine that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the surface of the splash plate of the component that forms a boundary for hot comb... | 02/28/2006 |
| 7000396 | Concentric fixed dilution and variable bypass air injection for a combustor A combustor for a gas turbine includes a combustor body having an aperture and a casing enclosing the combustor body and defining a passageway therebetween for carrying compressor discharge air. There is at least one injection tube for supplying an amount of the com... | 02/21/2006 |
| 6996992 | Gas collection pipe carrying hot gas A gas collection pipe (1) carrying hot gas establishes the connection between the combustion chambers (9) of a gas turbine plant and the flow channel (13) of the gas turbine. The gas collection pipe (1) has two inlet pipe connections (... | 02/14/2006 |
| 6964169 | Long life nozzle flap for aircraft turbojets The invention proposes a long life nozzle flap for aircraft turbojets. This flap is remarkable in that it is composed of a hollow tapered body (10) flattened in the transverse direction along straight geometric generating lines (11), the body (10 | 11/15/2005 |
