| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390830 | Cooling of auxiliary components | 31 |
| 20080202092 | Mixer for cooling and sealing air system of turbomachinery - A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections. The inner section is generally cylindrical in cross section and has a plurality of holes therein. The angle between the direction of the bypass flow and the direction of the third flow, when the bypass flow meets the third flow in the mixer, is less than about 90 degrees. | 08-28-2008 |
| 20080245051 | Means for cooling a bearing assembly - Means for cooling a bearing assembly supporting a rotor stage of a gas turbine engine after engine shutdown. The engine comprises a combustion section, a compressor for the delivery of air to the combustion section, and a bearing assembly supporting a rotor stage. The means for cooling a bearing assembly comprises a means operable to generate a signal representative of turbine duct temperature immediately prior to engine shutdown, a means for determining the duration for cooling after engine shutdown as a function of the signal representative of turbine duct temperature, and the compressor operable as a cooling means to deliver cooling air to the rotor stage after engine shutdown. Thereby the amount of heat conducted to the bearing assembly is limited such that the temperature of the bearing assembly is limited to below a predetermined temperature. | 10-09-2008 |
| 20090126335 | COOLING STRUCTURE - In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another. | 05-21-2009 |
| 20090133378 | Combustion Chamber and Gas Turbine Installation - A combustion chamber having a burner and a burner insert surrounding the burner while leaving a gap open towards the combustion chamber interior is provided. The burner insert comprises a carrier and a burner insert wall located in front of the carrier towards the combustion chamber interior, wherein a flow passage connected to a cooling-fluid source is formed between the carrier and the burner insert wall. The flow passage opens out into the gap between the burner and the burner insert and is otherwise sealed off from the combustion chamber interior. | 05-28-2009 |
| 20090188232 | THERMAL MANAGEMENT SYSTEM INTEGRATED PYLON - A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placement schemes. | 07-30-2009 |
| 20100011739 | APPARATUS AND METHOD FOR DRAWING OFF AND RECIRCULATING A COOLING STREAM - A device and method for drawing off and recirculating cooling streams, specifically for drawing off and recirculating a cooling stream of fuel for cooling at least one aircraft engine accessory, is disclosed. The device having a tubular jacket part defining a flow cross-section through which a primary stream, specifically a fuel stream, flows by way of an extraction pipe which is positioned approximately in the center of the flow cross-section, or jacket part, in order to draw off a cooling stream from the primary stream, by way of a hollow strut extending in the radial direction to divert this cooling stream from the device with the aid of the extraction pipe and to supply it to at least one accessory to be cooled, and by way of a return opening to recirculate the cooling stream directed through the accessory for cooling purposes to the primary stream. | 01-21-2010 |
| 20100107593 | Integrated Cooling, Heating, and Power Systems - One exemplary embodiment of this invention provides a single-effect absorption chiller including an absorber operatively connected to a solution heat exchanger and a generator, and a condenser in fluid communication with the absorber, wherein the absorber is sized and configured to receive a feed of water from a source of water and to transfer heat to the feed of water and then to convey the feed of water to the condenser without further heat conditioning of the feed of water prior to its entry into the condenser, and wherein the condenser is sized and configured to receive the feed of water from the absorber and to transfer heat to the feed of water, thereby cooling the condenser without resorting to an external heat exchanger such as a conventional cooling tower. | 05-06-2010 |
| 20100223902 | THERMOELECTRICALLY COOLED COMPONENTS FOR DISTRIBUTED ELECTRONICS CONTROL SYSTEM FOR GAS TURBINE ENGINES - A gas turbine engine control component includes at least one electronic device, electronics such as an integrated circuit associated with the device, and a thermoelectric cooler for cooling the electronics mounted in a compartment. The thermoelectric cooler may be disposed in or on a wall of the compartment with a heat sink connected to a hot side of the thermoelectric cooler and a cold side of the thermoelectric cooler exposed to an interior of the compartment. Data about and/or operating instructions for the device may be stored in memory on the integrated circuit. The data may be calibration information for the device. A bus connector is connected to the integrated circuit for transferring operating instructions and/or data from the integrated circuit out and/or out of the component. A controller or control system incorporating these devices and components have the devices electronically connected to the integrated circuit. | 09-09-2010 |
| 20110030332 | SYSTEM AND METHOD FOR LIQUID AIR PRODUCTION, POWER STORAGE AND POWER RELEASE - Systems and methods for storing and releasing energy comprising directing inlet air into a vertical cold flue assembly, a portion of moisture being removed from the air within the cold flue assembly. The air is directed out of the cold flue assembly and compressed. The remaining moisture is substantially removed and the carbon dioxide is removed from the air by adsorption. The air is cooled in a main heat exchanger such that it is substantially liquefied using refrigerant loop air. The substantially liquefied air is directed to a storage apparatus. The refrigerant loop air is cooled by a mechanical chiller and by a plurality of refrigerant loop air expanders. In energy release mode, working loop fluid warms the released liquid air such that the released liquid air is substantially vaporized, and the released liquid air cools the working loop fluid such that the working loop fluid is substantially liquefied. A portion of the released liquid air is directed to the at least one generator and used as bearing air for the at least one generator. The substantially vaporized air is directed to a combustion chamber and combusted with a fuel stream. Combustion gas may be directed from the combustion chamber to at least one expander and expanded in the expander, the expanded combustion gas split into a first portion and a second portion, the first portion being relatively larger than the second portion. The first portion may be directed to a first heat exchanger, and the second portion may be directed to a second heat exchanger such that the second portion heats and substantially vaporizes the released liquid air. | 02-10-2011 |
| 20110173947 | SYSTEM AND METHOD FOR GAS TURBINE POWER AUGMENTATION - A gas turbine power augmentation system and method are provided. The system includes a chiller, a controller, a heat exchanger, and a gas turbine inlet air flow. The chiller may be operable to chill a coolant flow using energy from a heat source. The controller may be operably connected to the chiller and configured to regulate operation of the chiller in relation to at least one environmental condition. The heat exchanger may be in fluid communication with the chiller and configured to allow the coolant flow to pass through the heat exchanger. The gas turbine inlet air flow may be directed through the heat exchanger before entering a gas turbine inlet, allowing the air flow to interact with the coolant flow, thereby cooling the air flow. | 07-21-2011 |
| 20110252764 | Systems and methods for thermal management in a gas turbine powerplant - A thermal management system for a gas turbine powerplant with an engine oil line and an engine fuel line incorporates a heat transfer control module that includes a reversible heat pump with a heat pump compressor for circulating working fluid in forward and reverse directions through a working fluid line of the heat pump. The heat control module also includes a first heat exchanger having a heat exchange path for the working fluid between the compressor and a heat pump expansion valve and another heat exchange path for the engine oil. A second heat exchanger has a heat exchange path for the working fluid between the compressor and the expansion valve and another heat exchange path for the engine fuel. The heat pump can be operated in forward or reverse directions depending on whether heat is to be transferred from the engine oil or the fuel to the heat pump working fluid. In another embodiment an engine oil reservoir located between the first heat exchanger and the engine collects the oil before it is introduced to the engine and thus acts as a heat capacitor for the system. | 10-20-2011 |
| 20110271655 | SEPARATE COOLING PLATE FOR AIRCRAFT ENGINE ELECTRIC CONTROL - An assembly has an electrical control including electrical connectors and electric circuits. The electric circuits are programmed to control an aircraft engine. The electrical control is attached to a cooling plate, which includes internal fluid passages for circulating a cooling fluid, and providing cooling to the electrical control. In a separate feature, an electric element is mounted to a cooling plate that is in turn mounted to an outer housing of an engine. | 11-10-2011 |
| 20120023893 | COOLING DEVICE FOR HIGH TEMPERATURE FLUID, FLIGHT VEHICLE HAVING THE SAME AND COOLING METHOD FOR HIGH TEMPERATURE FLUID - Disclosed are a cooling device for high temperature fluid, a flight vehicle having the same and a cooling method for high temperature fluid, the cooling device including a heat exchanger configured such that fluid is introduced therein to be heat-exchanged with a refrigerant, and configured to vaporize the refrigerant by the heat exchange such that the fluid is discharged at temperature close to vaporization temperature of the refrigerant, a compressor connected to the heat exchanger and configured to compress the fluid discharged out of the heat exchanger, a turbine connected to the compressor and configured to expand the fluid compressed in the compressor to lower temperature of the compressed fluid, and a phase change heat exchanger connected to the turbine, storing a phase change material, and configured to cause heat exchange between the phase change material and the fluid discharged out of the turbine so as to control temperature of the discharged fluid, whereby a cooling device capable of minimizing influences by external environments can be achieved. | 02-02-2012 |
| 20120227371 | SYSTEM FOR COOLING AND PURGING EXHAUST SECTION OF GAS TURBINE ENGINE - A system is provided with a turbine exhaust strut configured to provide a bi-directional airflow. The turbine exhaust strut includes a first portion having a first flow passage configured to flow a fluid in a first direction between inner and outer exhaust walls of a turbine exhaust section, and a second portion having a second flow passage configured to flow the fluid in a second direction between the inner and outer exhaust walls of the turbine exhaust section. Furthermore, the first and second directions are opposite from one another. | 09-13-2012 |
| 20130036721 | Linear regenerator with circulating heat transfer surface - A regenerative heat exchanger for transferring heat from the exhaust gas to the intake working fluid of a prime mover and from the pressurized working fluid to the exhaust vapor of a heat pump. Application is especially useful in a system in which liquid air or nitrogen made by a heat pump provides compression cooling for a gas turbine prime mover. The heat exchanger employs circulating element heat transfer surface such as wire belts or ceramic balls, which circulate in turn through working fluid exhaust and intake channels while absorbing and rejecting heat between the two channels. Effectiveness exceeding 98% increases thermal efficiency of small low-pressure ratio gas turbines. | 02-14-2013 |
| 20130036722 | FUEL SYSTEM HAVING FUEL CONTROL UNIT AND HEAT EXCHANGER - A fuel system includes a fuel control unit having a fuel passage that extends between an inlet to at least one pump stage and an outlet at a metering valve that is operable to control fuel supply. A portion of the fuel passage extends through a heat exchanger. | 02-14-2013 |
| 20130097992 | INTEGRATED THERMAL MANAGEMENT SYSTEM AND ENVIRONMENTAL CONTROL SYSTEM FOR A GAS TURBINE ENGINE - A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler. | 04-25-2013 |
| 20130239541 | TURBINE NOZZLE SEGMENT AND CORRESPONDING GAS TURBINE ENGINE - A turbine nozzle segment of a turbo-machine includes a platform defining a segment of a boundary for a main fluid path, the platform having a section, particularly a trailing section of the platform. The section has a surface along which a main fluid flows during operation of the turbo-machine. The surface further includes a plurality of alternating elevations and depressions, wherein the elevations and the depressions both are arranged substantially perpendicular to a direction of a main fluid flow of the main fluid. | 09-19-2013 |
| 20130263570 | FLUID FLOW MACHINE ESPECIALLY GAS TURBINE PENETRATED AXIALLY BY A HOT GAS STREAM - In a fluid flow machine, especially a gas turbine, axially penetrated by a hot gas stream, the rotor shaft is surrounded by heat shield segments or by base plates of the rotor blades on the rotor side. In the heat shield segments and in the base plates, cooling air chambers are provided, communicating with each other and with a cooling air source, which chambers communicate at least partially with gaps which extend in the longitudinal direction or peripheral direction of the rotor shaft between adjacent rotor blades or between heat shield segments and adjacent base plates of the rotor blades. These gaps are closed off by sealing bands such that a cooling air entry into the hot gas stream is only possible at the ends of the base plates of the rotor blades pointing contrary to the flow direction. | 10-10-2013 |
| 20140196433 | GAS TURBINE ENGINE COMPONENT PLATFORM COOLING - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform. | 07-17-2014 |
| 20140331641 | METHOD FOR PRODUCING A NEAR-SURFACE COOLING PASSAGE IN A THERMALLY HIGHLY STRESSED COMPONENT, AND COMPONENT HAVING SUCH A PASSAGE - The invention refers to a method for producing a near-surface cooling passage in a thermally highly stressed component, which includes: a) providing a component which has a surface on a hot side in a region which is to be cooled; b) letting a channel into the surface; c) inserting a cooling tube into the channel; d) filling the channel, with the cooling tube inserted, with a temperature-resistant filling material in such a way that the inserted cooling tube is embedded into the filling material, leaving free an inlet and an outlet; and e) covering the channel, with the cooling tube embedded, with an anti-oxidation, temperature-stable cover layer. The method is inexpensive and can be used in a flexible manner in the most diverse situations in order to save cooling medium or to reduce the thermal load. | 11-13-2014 |
| 20140360155 | MICROCHANNEL SYSTEMS AND METHODS FOR COOLING TURBINE COMPONENTS OF A GAS TURBINE ENGINE - The present application and the resultant patent thus provide a microchannel system for cooling a hot gas path surface of a turbine. The microchannel system may include a turbine component having an outer surface extending along a hot gas path of the turbine, a microchannel defined within the turbine component and extending about the outer surface, and a number of pockets defined within the turbine component and positioned along the microchannel. The present application and the resultant patent further provide a method of forming a microchannel system for cooling a hot gas path surface of a turbine. The method may include the steps of forming a turbine component having an outer surface extending along a hot gas path of the turbine, defining a microchannel within the turbine component and extending about the outer surface, and defining a number of pockets within the turbine component and positioned along the microchannel. | 12-11-2014 |
| 20150020498 | COOLING COVER FOR GAS TURBINE DAMPING RESONATOR | 01-22-2015 |
| 20150033696 | TURBINE CASING FALSE FLANGE FLOW DIVERTER - A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface. | 02-05-2015 |
| 20150033697 | REGENERATIVELY COOLED TRANSITION DUCT WITH TRANSVERSELY BUFFERED IMPINGEMENT NOZZLES - A cooling arrangement ( | 02-05-2015 |
| 20150082767 | Passive Cooling System for Control Valve Actuators - The present application provides a passive control valve actuator cooling system to provide a flow of cooling air to a control valve actuator used with a gas turbine engine. The passive control valve actuator cooling system may include a turbine enclosure with a negative pressure therein, a radiation shield with a number of radiation shield outlets and the control valve actuator positioned therein, and a cooling air line extending from outside of the turbine enclosure to the radiation shield such that the negative pressure within the turbine enclosure pulls the flow of cooling air into and through the radiation shield so as to cool the control valve actuator. | 03-26-2015 |
| 20150082768 | SYSTEMS AND METHODS FOR FACILITATING SUBSTANTIALLY UNIFORM VENTILATION AIRFLOW INSIDE AN ENGINE ENCLOSURE OF A GAS TURBINE ENGINE - A diffuser assembly for a ventilation system is disclosed herein. The diffuser assembly may include a boundary defining an interior of the diffuser assembly. The diffuser assembly also may include at least one inlet to the interior of the diffuser assembly. The at least one inlet to the interior of the diffuser assembly may be in fluid communication with at least one ventilation fan. Moreover, the diffuser assembly may include an outlet from the interior of the diffuser assembly. The outlet from the interior of the diffuser assembly may be in fluid communication with an engine enclosure. In this manner, the outlet from the interior of the diffuser assembly may be configured to provide a flow of ventilation air from the at least one ventilation fan as a substantially uniform flow of ventilation air within the engine enclosure. | 03-26-2015 |
| 20150143792 | COMPONENTS WITH MULTI-LAYERED COOLING FEATURES AND METHODS OF MANUFACTURE - A manufacturing method includes providing a substrate having one or more grooves formed therein. One or more coatings having one or more grooves formed therein are disposed on the substrate and in fluid communication with the one or more grooves in the substrate. A cover coating is disposed on a portion of an outermost surface of the one or more coatings, having one or more cooling outlets formed therein and in fluid communication with the one or more grooves in the one or more coatings. The substrate, the one or more coatings and the cover coating define therein a cooling network for cooling a component. A component having a cooling network defined therein a substrate, one or more coatings disposed on at least a portion of the substrate, and a cover coating disposed over at least a portion of an outermost coating of the one or more coatings. | 05-28-2015 |
| 20160084109 | GAS TURBINE RING SEGMENT COOLING APPARATUS - A gas turbine shroud ring segment assembly ( | 03-24-2016 |
| 20160195018 | Turbine last stage rotor blade with forced driven cooling air | 07-07-2016 |
| 20160201558 | CONTROLLER COOLING ARRANGEMENT | 07-14-2016 |
