Class / Patent application number | Description | Number of patent applications / Date published |
060751000 | Having diffuser for air inlet | 28 |
20090293485 | DIFFUSERS, DIFFUSION SYSTEMS, AND METHODS FOR CONTROLLING AIRFLOW THROUGH DIFFUSION SYSTEMS - A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction. | 12-03-2009 |
20090308076 | AIR CYCLE MACHINE TURBINE OUTLET HEATED DIFFUSER - The turbine outlet heated diffuser may include a cavity positioned immediately downstream of an air cycle machine turbine. The turbine outlet heated diffuser may be designed to prevent or reduce ice formation at the turbine outlet by heating the diffuser wall. The cavity may receive a heated flow from an air cycle machine compressor discharge and provide a cavity outlet flow to a turbine inlet plenum. The design of the heated diffuser is such to minimize the cycle performance impact that results from the addition of an air cycle machine icing protection feature. | 12-17-2009 |
20100031663 | TURBOMACHINE WITH A DIFFUSER - A turbomachine comprising:
| 02-11-2010 |
20100037616 | Diffuser for Decelerating a Compressed Fluid - A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring is assembled from these sections. The ring defines one or more passages, the cross-section of which increases in the direction of flow of a fluid through the diffuser. The interface between adjacent sections is configured so that relative movement between the sections is prevented. The interface is configured to have a series of interlocking serrations along the axial length of the diffuser. In an embodiment, there are two arcuate sections involving two interfaces, and the peaks and troughs of the serrations of each of the two sections are arranged at an angle to a longitudinal axis of the diffuser. A small relative movement between the sections is achieved when the two angles at the two interfaces have opposite signs. | 02-18-2010 |
20100058768 | AXIAL DIFFUSOR FOR A TURBINE ENGINE - A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell. | 03-11-2010 |
20100101230 | Flow splitter for gas turbine engine - A splitter is disclosed that can be coupled with a splitter support and used within a diffuser of a gas turbine engine. The splitter includes apertures for receiving a portion of the splitter support. The splitter support includes support arms that are adapted to be slidingly received within the apertures of the splitter. | 04-29-2010 |
20100122536 | PLASMA FLOW CONTROLLED DIFFUSER SYSTEM - A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The plasma actuator is disposed at least partially proximate the second wall. The plasma actuator is adapted to generate an electric field to ionize a portion of air flowing through the flow passage. | 05-20-2010 |
20100229562 | REDUCED EXHAUST EMISSIONS GAS TURBINE ENGINE COMBUSTOR - A gas turbine engine combustor includes a plurality of main fuel injector assemblies, and a plurality of pilot fuel injector assemblies, that are arranged and configured to reduce exhaust gas emissions during engine operation. The plurality of main fuel injector assemblies are arranged in a substantially circular pattern of a first radius, and each includes an outlet port having a first divergence angle. The plurality of pilot fuel injector assemblies are arranged in a substantially circular pattern of a second radius. Each pilot fuel injector assembly is disposed between at least two main fuel injector assemblies, and each includes an outlet port having a second divergence angle. | 09-16-2010 |
20110056207 | DIFFUSER FOR TURBINE ENGINE INCLUDING INDENTED ANNULAR WEBS - A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser. | 03-10-2011 |
20110192166 | OUTLET GUIDE VANE STRUCTURE - An outlet guide vane structure | 08-11-2011 |
20110265483 | Combustor For A Turbine, and Gas Turbine Outfitted With A Combustor of This Kind - Combustor for a turbine, and gas turbine outfitted with a combustor. The combustor has a housing in which an air collecting chamber, a combustion antechamber, and a combustion chamber are formed. A combustor head plate is arranged in the housing so that the combustor head plate separates the combustion antechamber from the combustion chamber. A baffle plate is arranged in the combustion antechamber so that the baffle plate divides the combustion antechamber into a first sub-chamber adjoining an air supply fluidically connected with the air collecting chamber and a second sub-chamber adjoining the combustor head plate. Wherein baffle plate has a plurality of through-passages that fluidically connect the first sub-chamber with the second sub-chamber so that air that has flowed into the first sub-chamber from the air collecting chamber via the air supply can flow into the second sub-chamber via the through-passages and to a back surface of the combustor head plate facing the second sub-chamber. | 11-03-2011 |
20110296841 | GAS TURBINE ENGINE DIFFUSER - An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow channel between the corresponding plurality of vanes. The first side has at least one tapered surface extending from an inner radial position to an outer radial position. The distance between a tapered surface and a top side of the plurality of the vanes defines a depth of the air flow channel. The width of the air flow channel varies relative to the depth of the air flow channel along the length of the air flow channel. | 12-08-2011 |
20110314828 | BLEEDING OF AIR VIA THE DIFFUSER OF A CENTRIFUGAL COMPRESSOR OF A TURBINE ENGINE - Diffuser intended to straighten the flow of air issuing from a centrifugal compressor in a turbine engine, the said diffuser having a cylindrical shape and comprising a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part and a third part intended to open out into a downstream cavity, positioned downstream of the said diffuser and fed with air issuing from the said compressor, characterized in that the first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the said downstream cavity into communication with a bleed cavity situated upstream of the said diffuser. | 12-29-2011 |
20120167572 | GAS TURBINE ENGINE AND DIFFUSER - One embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and components thereof. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 07-05-2012 |
20130000308 | Diffuser Pipe and Assembly for Gas Turbine Engine - A diffuser pipe ( | 01-03-2013 |
20130042623 | CONICAL REVERSE-FLOW COMBUSTION CHAMBER FOR A TURBOMACHINE - Assembly consisting of a reverse-flow combustion chamber for a turbomachine and a diffuser intended to be positioned at the outlet of a centrifugal compressor and comprising two faces running parallel to one another, the said combustion chamber comprising a first annular part configured to bear at least one injection system and a second annular part extending beyond this first part so as to form a guide canal for turning back the direction in which the gases passing through the chamber flow, with reference to the axis of rotation of the said turbomachine, the axis Y-Y of the said first part being secant with the said axis of rotation, the assembly being characterized in that the said faces of the diffuser have a curved shape which evolves parallel to that of the outer wall of the chamber at its turn-back canal. | 02-21-2013 |
20140116056 | GAS TURBINE DIFFUSER WITH FLOW SEPARATOR - A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump region distal the inlet. The flow separator extends from the first wall into the annular cavity. | 05-01-2014 |
20140137559 | GAS TURBINE ENGINE COMBUSTOR WITH INTEGRATED COMBUSTOR VANE - A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber. | 05-22-2014 |
20140144145 | GAS TURBINE COMBUSTION CHAMBER - The present invention relates to a gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with several burners arranged spread over the circumference of the combustion chamber, and with air inlet recesses which in at least one radial plane are provided spread over the circumference on an outer combustion chamber wall and on an inner combustion chamber wall, where the burner is designed to form a flow provided with a swirl and where air inlet recesses assigned to a burner are dimensioned in differing size in order to generate airflows of differing size, characterized in that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl of the combustion chamber flow and is provided with flow guidance walls. | 05-29-2014 |
20140352313 | DIFFUSER STRUT FAIRING - A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction side portion extend between the top portion and the bottom portion. The exhaust diffuser strut faring further includes a flow manifold that is at least partially defined between the pressure side portion and the suction side portion. A plurality of openings is disposed along the suction side portion and are in fluid communication with the flow manifold. | 12-04-2014 |
20150068211 | RADIAL MIDFRAME BAFFLE FOR CAN-ANNULAR COMBUSTOR ARRANGEMENT HAVING TANGENTIALLY ORIENTED COMBUSTOR CANS - A can-annular gas turbine engine combustion arrangement ( | 03-12-2015 |
20160003260 | METHOD AND APPARATUS FOR SELECTIVELY COLLECTING PRE-DIFFUSER AIRFLOW - A diffuser for a gas turbine engine is provided that includes an outer shroud, an inner shroud, a multiple of struts between said outer shroud and said inner shroud to define an annular flow path, and a mid-span pre-diffuser inlet in communication with said annular flow path. | 01-07-2016 |
20160032778 | ROTATABLE FULL RING FAIRING FOR A TURBINE ENGINE - A turbine engine includes a full ring fairing having at least a first and second keyed feature. The full ring fairing is rotatable so that the second keyed feature is in the first keyed feature position relative to the turbine engine. | 02-04-2016 |
20160115971 | DIFFUSER PIPE WITH SPLITTER VANE - A compressor diffuser for a gas turbine engine includes a plurality of diffuser pipes each having a diverging tubular body defining a flow passage extending fully therethrough. The tubular body includes a first portion extending in a first direction, a second portion extending in a second direction different from the first direction, and a curved portion interconnecting the first portion and the second portion. At least one splitter vane extends into the flow passage and disposed at least partially within the curved portion of the tubular body. | 04-28-2016 |
20160146465 | NOZZLE GUIDE FOR A COMBUSTOR OF A GAS TURBINE ENGINE - A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings. | 05-26-2016 |
20160169049 | Pre-Diffuser Strut for Gas Turbine Engine | 06-16-2016 |
20160201688 | GAS TURBINE ENGINE DIFFUSER COOLING AND MIXING ARRANGEMENT | 07-14-2016 |
20170234538 | COMBUSTOR ASSEMBLY | 08-17-2017 |