Patent application number | Description | Published |
20080306617 | CORE OBJECT-ORIENTED TYPE SYSTEM FOR SEMI-STRUCTURED DATA - A type system employing structural subtyping is disclosed herein. A core type system supports several structural types, such as stream, choice, intersection and sequence. Also part of the core type system is a new invariant type, which denotes values whose dynamic type is the same as its static type, and type restrictions for limiting a range of a base type. Furthermore, a streamlined structural version of delegates, called structural delegates and a validation method thereof are introduce into the type system. To further facilitate type safety, strict statically checked interface casts are introduced. | 12-11-2008 |
20080313609 | CORE OBJECT-ORIENTED TYPE SYSTEM FOR SEMI-STRUCTURED DATA - A type system employing structural subtyping is disclosed herein. A core type system supports several structural types, such as stream, choice, intersection and sequence. Also part of the core type system is a new invariant type, which denotes values whose dynamic type is the same as its static type, and type restrictions for limiting a range of a base type. Furthermore, a streamlined structural version of delegates, called structural delegates and a validation method thereof are introduce into the type system. To further facilitate type safety, strict statically checked interface casts are introduced. | 12-18-2008 |
20100083238 | Binary manipulation of intermediate-language code - One or more embodiments, described herein, are directed towards a technology for performing transformations and/or modifications to managed byte code. In order to perform the transformations and/or modifications, a mutable programmable representation (MPR) is laid out. A programmer then performs an arbitrary adjustment using the MPR. | 04-01-2010 |
20100088669 | LOGICAL EXTENSIONS TO INTERMEDIATE CODE - An assembly aggregate comprising a virtual, logical view of an arbitrarily defined collection of intermediate code and metadata can be authored, factored, accessed, modified, and distributed. Multiple physical containers of assembly information can be aggregated to create a single logical assembly called an assembly aggregate. An assembly can thus be redefined as a logical view against (or projection over) the assembly aggregate. Such an assembly can be targeted to the requester: that is, an assembly can be redefined according to tool and/or execution context rather than conforming to explicit or implicit requirements enforced by the runtime. | 04-08-2010 |
20100281537 | SECURE MULTI-PRINCIPAL WEB BROWSER - A web browser operating system using a browser kernel places principals having different origins in separate principal instances, where each separate principal instance executes in a separate protection domain. Principal origin may be determined using the combination of protocol, domain name, and port. The browser kernel mediates communications between principal instances, and between the principal instances and the operating system. Within each principal instance, a browser runtime executes as a restricted operating system process (ROSP), while any plugins are executed as a separate ROSP. Renderings from each browser runtime are combined by the browser kernel for presentation to a user. | 11-04-2010 |
20110265067 | Automatic Parallelization in a Tracing Just-in-Time Compiler System - A tracing just-in-time (TJIT) compiler system is described for performing parallelization of code in a runtime phase in the execution of code. Upon detecting a hot loop during the execution of the code, the compiler system extracts trace information from sequentially recorded traces. In a first phase, the compiler system uses the trace information to identify at least one group of operation components that can be operated on in a parallel manner. In a second phase, the compiler system provides instructions which allocate the group of operation components to plural processing resources. A native code generator module carries out those instructions by recompiling native code that directs the operation of a native system to perform parallel processing. The compiler system terminates a group if it encounters program data in a loop iteration that is not consistent with previously encountered predicated information (upon which it records a new trace in a sequential manner). | 10-27-2011 |
20120167042 | CONTEXTUALLY INTELLIGENT CODE EDITING - This document describes techniques for contextually intelligent code editing. In at least some embodiments, the techniques are network-based and can use client-server interactions to develop programming code. For example, input to a local programming environment of a client can be transmitted to a server. A functionality at the server can inspect the input and determine programming options (e.g., programming terms and/or phrases) that are contextually valid in the local programming environment. A list of the programming options can then be transmitted to the client and presented via a user interface. In some embodiments, a selection of one of the programming options can cause the programming option to be populated to the local programming environment, e.g., as part of a user interface associated with the local programming environment. In at least some embodiments, the list of programming options can be cached locally on the client for quick retrieval. | 06-28-2012 |
Patent application number | Description | Published |
20090293449 | Gas-Turbine engine in particular aircraft engine - On a gas-turbine engine, in particular an aircraft engine, with a fan, a fan casing and a fan duct as well as with high-pressure and low-pressure turbines arranged behind each other in flow direction in the casing of the engine, the auxiliaries connected are to be operated with only a small increase in engine power. For this purpose in the flow direction of the airflow ( | 12-03-2009 |
20100080700 | Two-shaft engine for an aircraft gas turbine - On a two-shaft engine for an aircraft gas-turbine with a central low-pressure shaft, with a high-pressure shaft co-axially surrounding the low-pressure shaft and with bearing units supporting the shafts on the engine casing, the bearing loads of the high-pressure shaft are directed upstream towards the fan and the bearing loads of the low-pressure shaft are directed downstream. In order to reduce axial bearing load of the high-pressure bearing unit, the oppositely directed bearing loads of the low-pressure shaft ( | 04-01-2010 |
20130098179 | ACCESSORY GEARBOX DEVICE FOR A JET ENGINE - The present invention proposes an accessory gearbox ( | 04-25-2013 |
20150135660 | JET ENGINE COMPRISING A DEVICE FOR SPRAYING OIL INTO AN AIR-OIL VOLUME FLOW - The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area designed movable relative to the wall area. | 05-21-2015 |
20150135663 | JET ENGINE COMPRISING A DEVICE FOR SPRAYING OIL - The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area rigidly connected to the wall area. | 05-21-2015 |
20150260563 | STRUCTURAL UNIT FOR ARRANGEMENT ON A HYDRAULIC FLUID TANK OF A JET ENGINE - The present invention proposes a structural unit ( | 09-17-2015 |
20150321130 | DEVICE OF AN AIRCRAFT ENGINE FOR SEPARATING OIL FROM AN AIR-OIL VOLUME FLOW - A device of an aircraft engine for separating oil from an air-oil volume flow and an apparatus for introducing oil into the air-oil volume flow. An outlet area of the apparatus for introducing oil is provided in a closed line section, into which the air-oil volume flow can be introduced via an inlet area. In accordance with the invention, a flow cross-section of the line section downstream of the outlet area of the apparatus tapers at least partially like a nozzle and at least in some sections inside a confusor area. | 11-12-2015 |
20160065106 | AIRCRAFT ENGINE AND METHOD FOR OPERATING AN AIRCRAFT ENGINE - An aircraft engine includes at least one electrical apparatus, which can be driven by a driveshaft in order to generate electrical energy. A hydrodynamic torque converter, with guide blades, which can be adjusted via a mechanism, is arranged between the driveshaft and the electrical apparatus. The guide blades are adjusted as a function of a rotational speed of the driveshaft, wherein the rotational speed of a shaft of the electrical apparatus operated as a generator can be adjusted, essentially within a predefined rotational speed range, via the adjustment of the guide blades. | 03-03-2016 |
20160076399 | TANK DEVICE OF AN AERO ENGINE WITH AN APPLIANCE FOR INTRODUCING OIL - A tank device of an aero engine, which has an inlet appliance for the supply of an air-oil volume flow into a tank space of the tank device, a separation appliance for the separation of oil from the air-oil volume flow that is supplied to the tank space, a conduit area which is confined by at least one wall and in which an air-oil volume flow can be guided in the area of the tank space at least in certain areas, and an outlet appliance, in the area of which a volume flow can be discharged via a valve appliance from the tank space of the tank device. At least one appliance for introducing oil is provided, by means of which oil can be supplied into the area of the conduit area substantially against a flow direction of the air-oil volume flow which is forming during operation in the conduit area. | 03-17-2016 |
20160090988 | AIRCRAFT ENGINE WITH A COMPRESSOR DEVICE - What is described is an aircraft engine with a compressor device and with a fan device. In the area of a compressor shaft, the compressor device is connected via an epicyclic gear to a fan shaft. A planetary web is operatively connected via bearing devices to the planetary gears. A ring gear is coupled with the fan shaft and a sun gear of the epicyclic gear is coupled with the compressor shaft, while the planetary carrier is held at the housing side in a torque-proof manner. The ring gear is connected via a flexible connection device to the fan shaft and/or the planetary carrier is connected via a flexible connection device to the housing. In the area of the connection device, movements between the ring gear and the planetary gears and/or between the planetary carrier and the housing can be at least approximately compensated in the radial and the axial direction. | 03-31-2016 |
20160097292 | GAS TURBINE HAVING AT LEAST TWO SHAFTS DESIGNED AS HOLLOW SHAFTS AT LEAST IN SOME AREAS AND ARRANGED COAXIALLY RELATIVE TO ONE ANOTHER - The present invention describes a gas turbine having two shafts, which are rotatably mounted using bearing devices in the area of a casing. An intermediate shaft sealing device is arranged between the bearing devices, which includes a sealing element connected to a first shaft, in which a further sealing element connected to the second shaft radially engages. An operating pressure is applied, in the area limited by the shafts in the axial direction of the shafts, to facing effective areas of the sealing elements, while the pressure prevailing in the area outside the shafts in the axial direction acts on effective areas of the sealing elements facing away from one another. A ratio between the outer diameters limiting the facing effective areas and the inner diameters likewise limiting these effective areas is in each case greater than or equal to 1.25. | 04-07-2016 |
Patent application number | Description | Published |
20140150401 | GEARED COMPRESSOR FOR GAS TURBINE ENGINE - A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies. | 06-05-2014 |
20140161591 | LUBRICANT SYSTEM - An aircraft engine having a fan or propeller stage mounted to a planetary gearing system through a planetary gearing output drive shaft is provided with a lubricant system having a seal with lubricant delivery chamber for receiving a lubricant and a sealing surface sealing against a rotatable shaft, the rotatable shaft has a hollow interior and an opening in registration with the delivery chamber. The lubricant system has a lubricant pump in fluidical communication with and downstream of the opening. | 06-12-2014 |
20140373555 | ACCESSORY MOUNTING FOR A GAS TURBINE ENGINE - A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine. | 12-25-2014 |
20150240931 | GEARING ARRANGEMENT - A cylindrical double helix gear having an axis and a unitary gear arrangement extending about the axis, wherein the gear arrangement has two axially spaced gear portions with each gear portion comprising a plurality of gear teeth extending about a radial outer surface of the gear arrangement, wherein the gear portions are connected by a flexible spacer portion configured to allow relative movement between the gear portions. | 08-27-2015 |
20160097330 | GAS TURBINE ARCHITECTURE - A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox. | 04-07-2016 |
20160097331 | GAS TURBINE ARCHITECTURE - A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox. | 04-07-2016 |
Patent application number | Description | Published |
20160071052 | STOCK MONITORING - A stock monitoring system, for monitoring items of stock in one or more storerooms for stock items. The system includes a portable device (e.g. PDA), the portable device including a first processor and, coupled thereto, a first wireless transceiver for short-range communication, the portable device being adapted to receive user inputs from a first user. A second wireless transceiver is coupled to the first processor, the second wireless transceiver being adapted for long-range wireless communications (e.g. 3G) with a remote system. The first processor is operable for receiving a user ID of a second user, and receiving one or more further inputs, at least a first input being received via the first wireless transceiver and including item data corresponding to an item, and at least a second user input being from the first user and associating the item with the second user. The first processor is operable for transmitting to the remote system via the second wireless transceiver, at least the item data, associated with the user ID. The system may further comprising an intermediate unit, the intermediate unit including a second processor and, coupled thereto, a reader and a wireless transmitter, the reader and/or wireless transmitter being adapted for short-range communication. The second processor may be operable, upon reading the user ID from an ID card of the second user by the reader, for transmitting the user ID user via the wireless transmitter, e.g. for a predetermined period. The first processor may be operable for receiving a user ID of a second user via the first wireless transceiver. Receiving the first input may comprises receiving the item data following placing of the portable device in the vicinity of a tag, the tag being mounted on or associated with the item and embodying encoded item data corresponding to the item. The reader, wireless transmitter and/or the first wireless transceiver may comprise a near field communication (NFC) device, and the tag may comprise a NFC RFID tag. A method, portable device and intermediate unit are also disclosed. | 03-10-2016 |