Matches 1 - 50 out of 155 1 2 3 4 >


Match Document Document Title
US20110120134 GAS TURBINE COMBUSTOR  
An annular combustor for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume, an intermediate volume and an aft volume. The...
US20150176843 COMBUSTION CHAMBER  
A double wall structured combustor having an outer wall having an inner surface and an outer surface and an inner wall comprising a plurality of tiles. Each tile has at least one interlocking...
US20150159871 GAS TURBINE ENGINE WALL  
A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole...
US20140250894 DUAL-WALL IMPINGEMENT, CONVECTION, EFFUSION (DICE) COMBUSTOR TILE  
A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and...
US20120144834 Gas Turbine Combustion Chamber  
A gas turbine combustion chamber has a housing (1), a flame tube (2) received therein, and a perforated plate (3) which at least partially surrounds the latter and which is fastened at both of its...
US20130340437 TURBINE ENGINE COMBUSTOR WALL WITH NON-UNIFORM DISTRIBUTION OF EFFUSION APERTURES  
A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The...
US20140007580 RETAINING COLLAR FOR A GAS TURBINE COMBUSTION LINER  
A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement...
US20110048024 GAS TURBINE COMBUSTOR WITH QUENCH WAKE CONTROL  
A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber and includes a circumferential row of a plurality of...
US20090084110 COMBUSTOR SYSTEMS WITH LINERS HAVING IMPROVED COOLING HOLE PATTERNS  
A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction.
US20150241063 COMBUSTOR WITH GROMMET HAVING PROJECTING LIP  
A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body...
US20110000215 Combustor Can Flow Conditioner  
The present application provides a combustor for a gas turbine engine. The combustor may include a combustor can with a number of nozzles therein and a flow conditioner positioned around the...
US20140116059 HOT GAS SEGMENT ARRANGEMENT  
A hot gas segment arrangement, especially for a combustion chamber of a gas turbine, that includes at least one hot gas segment, which is removably mounted on a carrier, and is subjected at its...
US20140116058 ASSEMBLIES AND APPARATUS RELATED TO COMBUSTOR COOLING IN TURBINE ENGINES  
A combustor of a combustion turbine engine is described. The combustor may include an inner radial wall, which defines a combustion chamber downstream of a primary fuel nozzle, and an outer radial...
US20150121885 Gas Turbine Combustor  
There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural...
US20130098063 COOLNG STRUCTURE FOR RECOVERY-TYPE AIR-COOLED GAS TURBINE COMBUSTOR  
In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air...
US20100037622 Contoured Impingement Sleeve Holes  
A combustor for use with a gas turbine. The combustor may include liner, an impingement sleeve, and with the liner and the impingement sleeve defining an airflow channel. The impingement sleeve...
US20060016191 Combined effusion and thick TBC cooling method  
A method for combined effusion and thick TBC cooling comprises a providing a substrate, depositing a thick TBC onto the substrate and laser drilling an array of effusion holes through the TBC...
US20110005233 COMBUSTION CHAMBER HEAD OF A GAS TURBINE  
A combustion chamber head of a gas turbine has a confinement enclosing a dampening volume (207) and including a combustion chamber-opposite confinement (206) and a combustion chamber-side...
US20140290258 METHOD FOR THE ARRANGEMENT OF IMPINGEMENT COOLING HOLES AND EFFUSION HOLES IN A COMBUSTION CHAMBER WALL OF A GAS TURBINE  
A method for the arrangement of effusion holes and impingement cooling holes in a combustion chamber wall including: distribution of the effusion holes in the surface to be cooled in accordance...
US20140238030 IMPINGEMENT-EFFUSION COOLED TILE OF A GAS-TURBINE COMBUSTION CHAMBER WITH ELONGATED EFFUSION HOLES  
The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement...
US20090199563 Scalable pyrospin combustor  
An axial-flow pyrospin combustor comprises inner and outer combustor liners and a plurality of pyrospin effusion holes. The inner liner is coaxially mounted inside the outer liner, about a central...
US20110126543 COMBUSTOR PANEL ARRANGEMENT  
A combustor module for a gas turbine engine is provided that includes a first annular liner assembly extending along a longitudinal axis of the engine. The first annular liner assembly includes a...
US20140238031 COMBUSTOR LINER  
The invention is a combustor liner (12) of a dual wall cooling structure including an inner wall section (30) configured to surround a combustion region (13) and in which a plurality of effusion...
US20060037323 Film effectiveness enhancement using tangential effusion  
Film effectiveness enhancement is provided by a plurality of tangentially angled effusion holes in a combustor liner. The effusion holes positioned in the initial flow region at the start of the...
US20140238029 FLOW CONDITIONER IN A COMBUSTOR OF A GAS TURBINE ENGINE  
A combustor in a gas turbine includes a liner having an interior volume defining a main combustion zone, a fuel injection system for delivering fuel into the main combustion zone, and a flow...
US20090120095 Combustion liner thimble insert and related method  
A gas turbine combustor liner has at least one circumferential row of air holes adapted to supply air in a radial direction into a combustion chamber within the liner. One or more of the air holes...
US20090071163 SYSTEMS AND METHODS FOR INSTALLING COOLING HOLES IN A COMBUSTION LINER  
A system and method for modification of cooling holes in a combustion liner to prevent cracking. The invention provides a portable combustion liner modification system for a gas turbine able to...
US20150101335 HOLE ARRANGEMENT OF LINERS OF A COMBUSTION CHAMBER OF A GAS TURBINE ENGINE WITH LOW COMBUSTION DYNAMICS AND EMISSIONS  
A gas turbine combustion chamber with an inner housing and an outer housing the inner housing having an inner wall element with a first hole arrangement and a second hole arrangement is provided....
US20120291442 WALL FOR A TURBOMACHINE COMBUSTION CHAMBER INCLUDING AN OPTIMISED ARRANGEMENT OF AIR INLET APERTURES  
A rotationally symmetrical wall for an aircraft turbomachine combustion chamber, including primary holes, dilution holes positioned downstream from the primary holes, and a plug installation...
US20100050650 GAS TURBINE ENGINE REVERSE-FLOW COMBUSTOR  
A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing...
US20130025293 TEMPERATURE MIXING ENHANCEMENT WITH LOCALLY CO-SWIRLING QUENCH JET PATTERN FOR GAS TURBINE ENGINE COMBUSTOR  
A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a...
US20130255265 COMBUSTORS WITH QUENCH INSERTS  
A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to...
US20110067406 IMPINGEMENT COOLED CROSSFIRE TUBE ASSEMBLY  
A crossfire tube assembly is configured for connecting adjacent combustion cans in a gas turbine, and includes a first tube segment having a first end and an opposite female end. A second tube...
US20090013695 Floatwell Panel Assemblies and Related Systems  
Floatwall panel assemblies and related systems are provided. A floatwall panel assembly includes a panel formed of porous ceramic material, the porous ceramic material exhibiting a porosity...
US20090071161 COMBUSTORS AND COMBUSTION SYSTEMS FOR GAS TURBINE ENGINES  
A combustion system includes a combustor having a forward annular liner having a first plurality of effusion holes, and an aft annular liner having a second plurality of effusion holes and forming...
US20100018211 Gas turbine transition piece having dilution holes  
A gas turbine transition piece includes a duct body having a forward end and an aft end, the duct body defining an enclosure for confining a flow of combustion products from a combustor to a...
US20130276450 COMBUSTOR APPARATUS FOR STOICHIOMETRIC COMBUSTION  
Gas turbine combustor with a specific fuel and oxidizer flow arrangement which provides high combustion efficiency for stoichiometric diffusion combustion in gas turbine applications operating...
US20090100840 COMBUSTION CHAMBER WITH OPTIMISED DILUTION AND TURBOMACHINE PROVIDED WITH SAME  
The invention relates to the field of turbomachines and concerns a combustion chamber (4) for which the dilution supply is optimised. The invention relates more particularly to optimisation of the...
US20130180252 COMBUSTOR ASSEMBLY WITH IMPINGEMENT SLEEVE HOLES AND TURBULATORS  
A combustor assembly for use with a gas turbine. The combustor assembly may include a liner, an impingement sleeve disposed about the liner, and an airflow channel defined between the liner and...
US20150260404 INTERFACE HEAT SHIELD FOR A COMBUSTOR OF A GAS TURBINE ENGINE  
A combustor for a gas turbine engine includes an interface shield between a first heat shield and a second heat shield.
US20090188256 EFFUSION COOLING FOR GAS TURBINE COMBUSTORS  
A combustor for a turbine engine includes an outer liner and an inner liner circumscribed by the outer liner to form a combustion chamber therewith in which an air and fuel mixture is combusted to...
US20130205793 GAS TURBINE ENGINE COMPONENT WITH IMPINGEMENT AND DIFFUSIVE COOLING  
A gas turbine engine component includes a gas path wall having a first surface and second surface and an impingement baffle having impingement holes for directing cooling fluid onto the first...
US20150260399 COMBUSTOR SECTION OF A GAS TURBINE ENGINE  
A liner for a gas turbine engine includes a cold side having a partition which extends therefrom to define a forward cavity and an aft cavity, each cavity having a plurality of film holes to...
US20120324863 COOLING SCHEME FOR AN INCREASED GAS TURBINE EFFICIENCY  
A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at...
US20140338346 COMBUSTOR SKIN ASSEMBLY FOR GAS TURBINE ENGINE  
A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion...
US20130205794 GAS TURBINE ENGINE COMPONENT WITH IMPINGEMENT AND LOBED COOLING HOLE  
A gas turbine engine component includes a gas path wall having a first and second opposing surfaces and a baffle positioned along the gas path wall. The baffle has impingement holes for directing...
US20120167574 GAS TURBINE ENGINE AND COMBUSTION LINER  
One embodiment of the present invention is a unique gas turbine engine combustion liner. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices,...
US20140318129 COMBUSTION CHAMBER  
The invention relates to a combustion chamber for burning an air-fuel mixture, a gas mixture or a gas-liquid mixture, including an outer casing; a flame tube located inside the outer casing and...
US20150007573 ANNULAR-COMBUSTION-CHAMBER BYPASS  
An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine...
US20150128602 HEAT SHIELD FOR A GAS TURBINE COMBUSTION CHAMBER  
The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall...

Matches 1 - 50 out of 155 1 2 3 4 >