Quotables
"There is practically no chance communications space satellites will be used to provide better telephone, telegraph, television, or radio service inside the United States."
T. Craven, FCC Commissioner ; 1961
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 8162609 | Turbine airfoil formed as a single piece but with multiple materials An air cooled turbine airfoil includes a multiple pass serpentine flow cooling circuit formed from a metallic printing process in which the blade can be printed from different materials as a single piece blade. The blade includes a multiple pass serpentine cooling c... | 04/24/2012 |
| 8147196 | Turbine airfoil with a compliant outer wall A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation in the outer layer is disclosed. The compliant dual wa... | 04/03/2012 |
| 8137067 | Turbine with interrupted purge flow A blade attachment apparatus for a turbine is provided and includes a member, which rotates about an axis of the turbine, including fore and aft disk posts that retain corresponding fore and aft turbine blades, respectively, fore and aft of a turbine nozzle and a ce... | 03/20/2012 |
| 8128365 | Turbine airfoil cooling system with rotor impingement cooling A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the turbine engine. The hollow, disc post body may be configured to pass co... | 03/06/2012 |
| 8118553 | Turbine airfoil cooling system with dual serpentine cooling chambers A cooling system for a turbine airfoil of a turbine engine having dual serpentine cooling channels, an inward serpentine cooling channel and an outward serpentine cooling channel, positioned within the airfoil. The inward serpentine cooling channel may receive cooli... | 02/21/2012 |
| 8109725 | Airfoil with wrapped leading edge cooling passage A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior... | 02/07/2012 |
| 8096766 | Air cooled turbine airfoil with sequential cooling An air cooled turbine airfoil, such as a rotor blade, with a sequential impingement cooling circuit that provides a high level of cooling with a low amount of cooling air. The airfoil is formed of a spar and shell construction in which the spar is formed from a seri... | 01/17/2012 |
| 8092176 | Turbine airfoil cooling system with curved diffusion film cooling hole A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes a first sidewall having a first radius of curva... | 01/10/2012 |
| 8092177 | Turbine airfoil cooling system with diffusion film cooling hole having flow restriction rib A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes first and second sections. The first section ma... | 01/10/2012 |
| 8079810 | Turbine airfoil cooling system with divergent film cooling hole A cooling system for a turbine airfoil of a turbine engine having at least one divergent film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The divergent film cooling hole includes a first section extending from an inner surface... | 12/20/2011 |
| 8066483 | Turbine airfoil with non-parallel pin fins A turbine blade for use in a gas turbine engine having an internal serpentine flow cooling circuit with pin fins and trip strips to promote heat transfer for obtaining a thermally balanced blade sectional temperature distribution. The serpentine flow cooling circuit... | 11/29/2011 |
| 8057177 | Turbine blade tip shroud A turbine blade that may include a tip shroud, the tip shroud having one or more cooling cavities defined therein, an airfoil, the airfoil having at least one coolant passage defined therein, and a plurality of exit apertures defined through an outer wall of at leas... | 11/15/2011 |
| 8052389 | Internally cooled airfoils with load carrying members A shroudless, air cooled gas turbine blade has an internal structure including load-carrying members that support the blade outer wall and divide the blade interior into cooling passages. The dimensions of the structure in particular the load-carrying members are ch... | 11/08/2011 |
| 8021113 | Twin-airfoil blade with spacer strips The invention relates to a blade possessing a leading edge and a trailing edge, the blade comprising a first airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, a second airfoil possessing an inner face and ... | 09/20/2011 |
| 7988418 | Microcircuits for small engines A turbine engine component for use in a small engine application has an airfoil portion having a root portion, a tip portion, a suction side wall, and a pressure side wall. The suction side wall and the pressure side wall have the same thickness. Still further, the ... | 08/02/2011 |
| 7980818 | Member having internal cooling passage Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a | 07/19/2011 |
| 7963744 | Cooling of pump rotors A rotor for a screw vacuum pump has a threaded body in which a central cavity is formed. A coolant is supplied to the cavity from a supply line provided in a shaft attached to the body. A coolant flow guide, which may be either separate from or at least partially in... | 06/21/2011 |
| 7938624 | Cooling arrangement for a component of a gas turbine engine A component, such as a blade, vane or combustor wall of a gas turbine engine comprises two walls defining a coolant passage and has an array of pedestals extending between the two walls for heat removal. Each pedestal changes in cross-section along its length. Alter... | 05/10/2011 |
| 7905706 | Turbine blade with spar and shell cooling A turbine blade of a spar and shell construction with multiple impingement cooling of the shell and cooling air channels formed in the platform to provide cooling for the platform and to provide purge air at the blade fillet to prevent ingestion of hot gas flow. The... | 03/15/2011 |
| 7871245 | Method for forming turbine blade with angled internal ribs Two pairs of ribs define three intermediate cooling chambers. Each rib in each pair extends parallel to the other rib in the pair. The ribs in a first pair are non-parallel to the ribs in a second pair. A first rib from the first pair is positioned spaced toward the... | 01/18/2011 |
| 7866947 | Turbine blade trip strip orientation A turbine component includes a coolant passage and a plurality of trip members that extend within the coolant passage. Each of the plurality of trip members includes an orientation relative to an expected flow direction through the coolant passage. At least three of... | 01/11/2011 |
| 7845905 | Hollow turbine blade A hollow turbine blade is provided including an airfoil profile which is formed by a suction-side profile wall and a pressure-side profile wall and around which a hot gas can flow and which has a profile height, directed along a blade axis, from a platform up to a p... | 12/07/2010 |
| 7837440 | Turbine bucket tip cap A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side. ... | 11/23/2010 |
| 7832986 | Multi-alloy turbine rotors and methods of manufacturing the rotors A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and... | 11/16/2010 |
| 7824156 | Cooled component of a fluid-flow machine, method of casting a cooled component, and a gas turbine A cooled component of a fluid-flow machine, through which a hot working medium flows, in particular a turbine blade of a gas turbine, in whose outer wall, to which the working medium can be applied, a cooling passage is provided, through which a cooling fluid can fl... | 11/02/2010 |
| 7758309 | Vane wheel of turbine comprising a vane and at least one cooling channel There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. The vane wheel having a plurality of turbulators is embod... | 07/20/2010 |
| 7704046 | Turbine blade with serpentine cooling circuit A turbine blade with a 5-pass serpentine flow cooling circuit to provide cooling for the blade. A first leg of the serpentine circuit is formed along the leading edge region of the blade, while the last leg is formed along the trailing edge region. The serpentine fl... | 04/27/2010 |
| 7637720 | Turbulator for a turbine airfoil cooling passage A turbulator used in a turbine blade of a gas turbine engine, the turbulators arranged along a wall of the cooling air passage in an inverted V-shape with a diffusion slot between adjacent turbulators. The turbulators have a frontal surface and a top surface that ar... | 12/29/2009 |
| 7581927 | Serpentine microcircuit cooling with pressure side features In accordance with the present invention, there is provided a turbine engine component having an airfoil portion with a pressure side and a suction side, a first microcircuit embedded in a wall forming the pressure side, an internal cavity containing a supply of coo... | 09/01/2009 |
| 7572103 | Component comprising a multiplicity of cooling passages A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections. Air jet interactions are generated at cooling passage intersections when air is passed through the cooling passages.... | 08/11/2009 |
| 7544044 | Turbine airfoil with pedestal and turbulators cooling A wall enclosing a hot gas path, the wall including a cooling cavity formed between an inner wall and an outer wall, and a plurality of pins extending between walls with a plurality of turbulators within the cooling passage to promote turbulence within the cooling a... | 06/09/2009 |
| 7544043 | Turbulator on the underside of a turbine blade tip turn and related method A turbine blade includes a shank portion and an airfoil portion with leading and trailing edges and a radially outer tip. An internal closed-loop cooling circuit is formed within the airfoil portion and includes at least one radial outflow passage and at least one r... | 06/09/2009 |
| 7513745 | Advanced turbulator arrangements for microcircuits A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an a... | 04/07/2009 |
| 7507071 | Cooling arrangement A cooling arrangement is provided in which an incident coolant flow is presented to a passage such that a proportion of that flow is diverted in order to create a standing relative overpressure in a chamber compared to the actual static pressure of the flow in the p... | 03/24/2009 |
| 7481621 | Airfoil with heating source An airfoil (26) for a gas turbine engine (10) having a source of heat for controlling a temperature gradient across the airfoil components. In one embodiment the airfoil includes a CMC outer body (28) defining an airfoil shape and a ceramic inne... | 01/27/2009 |
| 7445432 | Enhanced serpentine cooling with U-shaped divider rib A cooling passageway for use in an airfoil prtrion of a turbine engine component having a pressure side wall and a suction side wall is provided. The cooling passsageway comprises a serpentine flow passageway through which a cooling fluid flows. The passageway has a... | 11/04/2008 |
| 7431561 | Method and apparatus for cooling gas turbine rotor blades Methods and apparatus for cooling gas turbine rotor blades is provided. The blade includes an airfoil having an internal three pass serpentine cooling circuit having radially extending first, second, and third serpentine cooling cavities partially separated by, in a... | 10/07/2008 |
| 7413406 | Turbine blade with radial cooling channels A turbine blade is cooled by cooling air that flows through a radial cooling channel. The turbine blade includes a root and an airfoil. The flow of cooling air into the cooling channel is limited by a pre-meter orifice to provide a reduced pressure within the coolin... | 08/19/2008 |
| 7390167 | Compressor with centripetal air takeoff A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between... | 06/24/2008 |
| 7377747 | Turbine airfoil with integrated impingement and serpentine cooling circuit An airfoil for a gas turbine engine includes a generally radially-extending first cooling channel disposed between pressure and suction sidewalls adjacent the leading edge of the airfoil, and a generally radially-extending second cooling channel disposed aft of the ... | 05/27/2008 |
