| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390511 | Regenerator | 20 |
| 20090133380 | Gas Turbine Engine - A gas turbine engine is described having at least one compressor, at least one combustion chamber, at least one turbine, and having an exhaust heat exchanger, which is used for returning waste heat of the exhaust emissions to the compressed combustion air prior to entry of the same into a combustion chamber. The exhaust heat exchanger is used as a substrate for catalysts for use in the catalytic aftertreatment of the exhaust emissions, in order to thereby reduce the pollutant emissions, in particular NOx emissions, of the gas turbine engine. | 05-28-2009 |
| 20090260342 | GAS TURBINE - A gas turbine, in which compressed air that is compressed by a compressor ( | 10-22-2009 |
| 20090277154 | RECUPERATOR FOR AIRCRAFT TURBINE ENGINES - A recuperator for use in transferring heat from gas turbine exhaust gases to compressed air inlet gases before combustion. The recuperator utilizes a plurality (e.g., thousands) of microtubes or microchannels to form a heat exchanger having high effectiveness and low pressure drop while maintaining a low weight. Accordingly, the recuperator presented herein may be incorporated into light aircraft and helicopters without significantly compromising the performance thereof. | 11-12-2009 |
| 20090282804 | RECUPERATORS FOR GAS TURBINE ENGINES - An integrated heat exchanger assembly for a gas turbine engine includes a first flow path, a second flow path, and a third flow path. The first flow path is configured to be coupled to a compressor and a combustor, to receive compressed air from the compressor, and to supply the compressed air to the combustor. The second flow path is configured to be coupled to the compressor or the first flow path, or both, to receive compressed air therefrom, and to be coupled to the combustor and to supply compressed air thereto. The third flow path is disposed adjacent to the first and second flow paths, and is configured to be coupled to an exhaust section, to receive exhaust air therefrom, and to allow heat transfer from the exhaust air in the third flow path to the compressed air in the first and second flow paths. | 11-19-2009 |
| 20100043388 | Gas turbine engine arrangement - A gas turbine engine ( | 02-25-2010 |
| 20100180568 | Heat regeneration for a turbofan, a Velarus Propulsion - The invention adds details and alternate design supplementing the concept established with my patent application Ser. No. 12/013,431, Aircraft Propulsion System (APS). The APS ultimate fuel economy objectives requires long term design development, and this invention compromises some fuel economy for the expediency of short term implementation of a heat regeneration for turbofans via the re-arrangement of existing components and a few unique items readily designed. While this Velarus Propulsion (VPx) attains only 42% fuel economy, it retains the original APS fundamental architecture implementing heat regeneration for a turbofan engine, as well as the additional benefits of noise and emission abatement. This invention consists of the three APS technologies as follows:
| 07-22-2010 |
| 20100229525 | TURBINE COMBUSTION AIR SYSTEM - A turbine combustion air system includes a recuperator and a multi-zone combustor for accepting multiple combustion air streams at multiple temperatures. | 09-16-2010 |
| 20110146226 | RECUPERATOR FOR GAS TURBINE ENGINES - A recuperator for use in transferring heat from gas turbine exhaust gases to compressed air inlet gases before combustion. The recuperator utilizes a plurality of stacked foils that define microchannels to form a recuperator having high effectiveness and low pressure drop while maintaining a low weight. Accordingly, the recuperator presented herein may be incorporated into light aircraft and helicopters without significantly compromising the performance thereof. | 06-23-2011 |
| 20120216506 | GAS TURBINE ENGINE RECUPERATOR WITH FLOATING CONNECTION - A gas turbine engine recuperator including a plurality of independent arcuate segments, each segment having an inlet connection member designed to sealingly engage a plenum in fluid flow communication with the compressor discharge, and an outlet connection member designed to sealingly engage a plenum containing the combustor. One of the inlet and outlet connection members is a rigid member forming a rigid connection to the respective plenum, and the other of the inlet and outlet connection members includes a flexible member and forms a floating connection to the respective plenum, the floating connection allowing relative movement between the segment and a remainder of the gas turbine engine. | 08-30-2012 |
| 20130199152 | TURBINE ENGINE HEAT RECUPERATOR PLATE AND PLATE STACK - A heat recuperator includes a plurality of channel walls composed substantially of thermally-conductive material and supported in spaced-apart relation, defining fluid channels and interstices therebetween. The fluid channels receive at least one primary fluid flow and the interstices receive at least one secondary fluid flow so as to effect heat exchange between the two flows. In use, the plurality of channel walls are deformable by pressure differential between the primary and secondary fluid flows. When at least some of the channel walls are in a deformed state, the plurality of channel walls are stabilized through press fit engagement of mutually opposed contact regions formed in adjacent pairs of the channel walls. | 08-08-2013 |
| 20140260178 | AERODYNAMICALLY ACTIVE STIFFENING FEATURE FOR GAS TURBINE RECUPERATOR - A recuperator disposed in the exhaust duct of a gas turbine engine includes a plurality of recuperator plates arranged in a spaced-apart relationship to define therebetween a plurality of interstices and fluid channels, the plurality of interstices adapted to direct therethrough at least one first stream received at a leading plate edge of the recuperator plates and the plurality of fluid channels adapted to direct therethrough at least one second stream to effect heat exchange between the at least one first stream and the at least one second stream. Each recuperator plate includes, formed at the leading plate edge thereof, a first concavity extending along the leading edge in a direction substantially parallel to a longitudinal axis of the plate. The first concavity extends transversely to a direction of the at least one first stream flowing over each recuperator plate. | 09-18-2014 |
| 20140345249 | Regenerative Gas Turbine Combustor - A regenerative gas turbine combustor is provided that enable to reduce an amount of leakage of compressed air before preheating to compressed air after the preheating. | 11-27-2014 |
| 20150020500 | MICRO GAS TURBINE SYSTEM HAVNIG AN ANNULAR RECUPERATOR - A micro gas turbine system ( | 01-22-2015 |
| 20160025007 | PLATE HEAT EXCHANGER OF IMPROVED THERMAL EFFICIENCY FOR A TURBOSHAFT ENGINE - A plate heat exchanger having a plurality of plates with sinusoidal undulations and two chimneys positioned at two opposite corners of the plates. Modules are formed by assembling together pairs of plates, the modules being stacked so as to make contact via the inlet and outlet chimneys in order to form the heat exchanger. The sinusoidal undulations form a first angle β with the flow direction of the fluids in the heat exchanger, the first angle β increasing in the flow direction of a first fluid through the modules. Furthermore, each plate has two distribution zones for distributing the first fluid in the modules in the proximity of each inlet or outlet chimney in order to make the filling and the discharge of the modules by the first fluid more uniform. | 01-28-2016 |
| 20160047310 | HEAT STORAGE MECHANISM OF HEAT EXCHANGER - A heat storage mechanism, of a heat exchanger, which does not shorten the service life of the heat exchanger even when a facility using the heat exchanger is intermittently operated and which suppresses a decrease in efficiency at the time of restart of the facility, is provided. The heat storage mechanism for storing heat of a heat exchanger during stop of operation of a facility provided with the heat exchanger includes an outflow prevention unit configured to prevent outflow of an exhaust gas to the outside, which is a heating medium of the heat exchanger, during stop of operation of the facility is provided in an exhaust passage through which the exhaust gas is discharged to the outside. | 02-18-2016 |
| 20160108813 | ADDITIVE MANUFACTURED DUCTED HEAT EXCHANGER - A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core. | 04-21-2016 |
| 20160108814 | ADDITIVE MANUFACTURED DUCTED HEAT EXCHANGER SYSTEM WITH ADDITIVELY MANUFACTURED FAIRING - A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core. | 04-21-2016 |
| 20160169106 | GAS TURBINE SYSTEM | 06-16-2016 |
| 20160195017 | Recuperated Gas Turbine Engine | 07-07-2016 |
| 060390512 | Rotary heat exchanger | 1 |
| 20110314789 | REGENERATOR FOR A THERMAL CYCLE ENGINE - A regenerator ( | 12-29-2011 |
