Bizarre Patents
Combination Beverage Container and Spittoon
A combination beverage container and spittoon includes a bottom portion including outer wall and a first inner wall defining a spittoon space.
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| Application No. | Application Title | Issue Date |
| 20120128467 | INTEGRATED VARIABLE GEOMETRY FLOW RESTRICTOR AND HEAT EXCHANGER One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or v... | 05/24/2012 |
| 20110255952 | COMPRESSOR GAS FLOW DEFLECTOR AND COMPRESSOR INCORPORATING THE SAME A turbocharger compressor includes a compressor housing having a housing wall that includes a shroud that defines a central air channel and a compressor inlet in fluid communication with the central channel and an inlet duct. It also includes a compressor wheel configur... | 10/20/2011 |
| 20110194928 | BLOW-OFF SYSTEM FOR MULTI-STAGE TURBO COMPRESSOR The present invention relates to a blow-off system for a multi-stage turbo compressor that includes a plurality of blow-off pipes disposed according to respective stages of the multi-stage turbo compressor; a plurality of blow-off valves disposed correspondingly to the ... | 08/11/2011 |
| 20110027072 | BYPASS SYSTEM FOR PURGING AIR FROM A SUBMERSIBLE PUMP A submersible pump, and method of making the submersible pump, is disclosed. The pump comprises a housing, a plurality of impeller stages serially disposed in the housing from a bottom impeller stage to a top impeller stage, an impeller bypass hole extending through one... | 02/03/2011 |
| 20100316488 | MIXING HOTTER STEAM WITH COOLER STEAM FOR INTRODUCTION INTO DOWNSTREAM TURBINE Apparatus and methods are presented for mixing a high temperature steam, perhaps leaked from an upstream turbine, with the cooler steam from a lower temperature, downstream turbine and introducing the mixture into the downstream turbine.... | 12/16/2010 |
| 20100263371 | TURBINE INTAKE PRESSURE RELEASE STRUCTURE A turbine intake pressure release structure to control pressure release between a throttle and a first turbine boosted pressure outlet includes a pressure release valve which has a first pressure orifice, a second pressure orifice and a housing chamber, at least one con... | 10/21/2010 |
| 20100247292 | System and Method of Cooling Turbine Airfoils with Sequestered Carbon Dioxide A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide from a carbon dioxide source and a method of using a stream of carbon dioxide to cool hot gas path components. The turbine power generating system includes a compressor, a com... | 09/30/2010 |
| 20100247306 | GAS TURBINE ENGINE WITH 2.5 BLEED DUCT CORE CASE SECTION A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a structural wall.... | 09/30/2010 |
| 20100221102 | CORE REFLEX NOZZLE FOR TURBOFAN ENGINE A turbofan engine is provided that includes a core nacelle at least partially surrounded by a fan nacelle. The core nacelle includes a reflex nozzle providing a core exit. The core nacelle includes a contour on its exterior surface upstream from the reflex nozzle. The c... | 09/02/2010 |
| 20100196143 | AXIAL COMPRESSOR An axial compressor comprises a stator component and a rotor component, which cooperate to perform work on a fluid flow in a primary flow-passage defined by the stator and rotor components, the stator component and the rotor component further defining a secondary flow-p... | 08/05/2010 |
| 20100126183 | CMC MIXER WITH STRUCTURAL OUTER COWLING The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner s... | 05/27/2010 |
| 20100074736 | Thermal management system In one embodiment a gas turbine engine is disclosed having a heat exchanger at least partially disposed in a bypass duct. In one form the gas turbine engine is a high bypass ratio engine. The heat exchanger may be coupled with a directed energy weapon to provide coolant... | 03/25/2010 |
| 20100037623 | High Efficiency Turbine Engine A by-pass turbofan gas turbine engine, comprises: a by-pass fan with a by-pass fan outlet; a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet; a generally annular by-pass duct situated in a ... | 02/18/2010 |
| 20100034643 | Transition duct aft end frame cooling and related method A transition duct for a gas turbine includes a tubular body having a forward end and an aft end, the aft end surrounded by a frame component; an interior closure band within the aft end, covering interior top, bottom and side wall surfaces of the frame; and a plurality ... | 02/11/2010 |
| 20100034637 | FLUID FLOW MACHINE A fluid flow machine has a main flow path 2 which is confined by a hub 3 and a casing 1 and in which at least one row of blades 5 is arranged. A gap 11 is provided on at least one blade row 5 between a blade end and a main flow ... | 02/11/2010 |
| 20100000197 | IMPINGEMENT COOLING FOR TURBOFAN EXHAUST ASSEMBLY A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurality o... | 01/07/2010 |
| 20090259379 | REDUCED TAKE-OFF FIELD LENGTH USING VARIABLE NOZZLE A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstre... | 10/15/2009 |
| 20090204305 | TURBINE BYPASS CONTROL APPARATUS AND TURBINE BYPASS CONTROL METHOD A turbine bypass control method includes: a high-pressure side pressure controller configured to output a first operation amount signal corresponding to a valve opening; a low-pressure side pressure controller configured to output a second operation amount signal corres... | 08/13/2009 |
| 20090175716 | Integrated bypass engine structure One form of the present invention contemplates an apparatus comprising a gas turbine engine core, a gearbox accessory mounted to the engine core and substantially enclosed by an inner fairing; a nacelle having a plurality of panels, wherein the nacelle panels substantia... | 07/09/2009 |
| 20090155056 | DEVICE FOR BLEEDING AIR FROM A TURBOMACHINE COMPRESSOR A turbomachine compressor, such as a high-pressure compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor, a screen sheet of annular sh... | 06/18/2009 |
| 20090148272 | TIP TURBINE ENGINE AND OPERATING METHOD WITH REVERSE CORE AIRFLOW A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the ... | 06/11/2009 |
| 20090116955 | TURBINE ENGINE COMPRISING MEANS FOR HEATING THE AIR ENTERING THE FREE TURBINE The invention relates to a turbine engine (10), particularly for a helicopter, comprising a gas generator (12) and a free turbine (14) rotated by a gas flow (F) generated by the gas generator. The invention is character... | 05/07/2009 |
| 20090092480 | GAS TURBINE ENGINE HAVING CORE AUXILIARY DUCT PASSAGE A gas turbine engine system includes a nacelle assembly, a core engine and a mixer disposed between the nacelle assembly and the core engine. The core engine includes a core passage and a core auxiliary duct passage. The core auxiliary duct passage includes an inlet for... | 04/09/2009 |
| 20090067988 | Mixer for cooling and sealing air system for turbomachinery A system for mixing flows from a compressor is provided. The system comprises an ejector that combines a first flow and a second flow, from the compressor, into a third flow. A bypass flow is connected between the first flow and the third flow. A mixer combines the bypa... | 03/12/2009 |
| 20090053043 | ATTACHMENT INTERFACE FOR A GAS TURBINE ENGINE COMPOSITE DUCT STRUCTURE A composite gas turbine engine duct receives a support ring that operates as an interface arrangement for attachment of engine system components. The support ring interfaces with the composite duct through a fastener shear load arrangement to provide a structurally soun... | 02/26/2009 |
| 20090047121 | INTERNAL COMBUSTION ENGINE SYSTEM HAVING A POWER TURBINE WITH A BROAD EFFICIENCY RANGE An engine system incorporating an air breathing, reciprocating internal combustion engine having an inlet for air and an exhaust for products of combustion. A centripetal turbine receives products of the combustion and has a housing in which a turbine wheel is rotatable... | 02/19/2009 |
| 20090022579 | BURN RESISTANT ORGANIC MATRIX COMPOSITE MATERIAL A burn resistant composite article includes at least one composite layer having first fibers within a first organic resin matrix. At least one burn resistance layer is disposed adjacent the at least one composite layer. The burn resistance layer includes second fibers w... | 01/22/2009 |
| 20090007567 | Dual Flow Turbine Engine Equipped with a Precooler The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in external contact with the cold flow (9) exiting the fan duct c... | 01/08/2009 |
| 20090010752 | PUMP AND METHOD A pump for moving a liquid including a rotor rotatable within a housing and slidable relative to the housing between a first axial rotor position during normal pump operation and a second axial rotor position during a pump inoperative condition.... | 01/08/2009 |
| 20090004032 | Deswirl mechanisms and roller bearings in an axial thrust equalization mechanism for liquid cryogenic turbomachinery Vane, fin, and hole arrangements establish a predetermined reduced swirl at the inlet of mechanical seals and the inlet of a variable axial orifice gap which act in harmony as an axial thrust equalizing system for use in liquid cryogenic turbines and pumps. In said esta... | 01/01/2009 |
| 20090000306 | Stator assembly including bleed ports for turbine engine compressor A stator assembly for a turbine engine is disclosed. The stator assembly has a stator support ring, a plurality of stator vanes protruding radially inwardly from the stator support ring, and at least one bleed port disposed on the stator support ring between at least tw... | 01/01/2009 |
| 20080298953 | WASTEGATE ASSEMBLY A wastegate assembly (200) for a turbocharger (101) or the like is provided having a support plate (300), an actuator (275), a linkage (250) operably connected to the actuator (275), and a valve plate (225) operably conne... | 12/04/2008 |
| 20080253879 | Blower for vehicles The present invention relates to a blower for vehicles, which includes guide walls formed on a bypass passageway formed between a scroll case and an outer case to send the indoor air and the outdoor air to a lower suction opening of the scroll case, thereby reducing suc... | 10/16/2008 |
| 20080247866 | Compressor and Compressor Housing A housing is incorporated as part of a compressor having blades that impart to a fluid a momentum along a main gas flow direction and a swirl. The housing includes a channel that has at least one channel wall and defines an axis substantially aligned with the main gas f... | 10/09/2008 |
| 20080232960 | Fluid return in the splitter of turbomachines with bypass-flow configuration A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing wit... | 09/25/2008 |
| 20080178591 | ARRANGEMENT OF A TWO STAGE TURBOCHARGER SYSTEM FOR AN INTERNAL COMBUSTION ENGINE Arrangement of a two stage turbocharger system for an internal combustion engine comprising an intake manifold and an exhaust manifold, comprising a low-pressure turbocharger, a high-pressure turbocharger and a bypass duct in flow communication with an outlet of the low... | 07/31/2008 |
| 20080175703 | ELECTRIC TURBINE BYPASS FAN AND COMPRESSOR FOR HYBRID PROPULSION An electric turbine compressor fan for hybrid propulsion wherein the compressor contains one or more rotor stages (compressor and diffuser), each being driven by one or more electric ring motors, such that the compressor rotor stages are designed and tuned more precisel... | 07/24/2008 |
| 20080118341 | WIDE FLOW COMPRESSOR WITH DIFFUSER BYPASS A centrifugal compressor is modified by forming a bypass between the leading edge of the compressor diffuser and a point downstream from the throat of the diffuser. The bypass may be unidirectional or bi-directional. In a bi-directional embodiment, an operable flow rang... | 05/22/2008 |
| 20080118348 | TURBOFAN GAS TURBINE ENGINE AND NACELLE ARRANGEMENT The arrangement comprises a fan by-pass duct located within the nacelle and having an inlet and an outlet. The outlet is generally oriented substantially radially and at an intermediary location along the nacelle. The nacelle has an aft section with an initially convex ... | 05/22/2008 |
| 20080115504 | Bleed Structure For A Bleed Passage In A Gas Turbine Engine A bleed structure for a bleed passage in a gas turbine engine includes a first wall portion defining a first side of an opening for the passage, and a second wall portion defining a second side, opposite the first side of the opening. The first and second wall portions ... | 05/22/2008 |
