Patent application number | Description | Published |
20110186176 | HOSE FUEL NOZZLE - A fuel hose nozzle for filling a tank having a filler the tank with liquefied petroleum gas has a tubular valve housing extending along an axis and having an outer end, a tubular valve guide axially shiftable in the valve housing between a front position and a rear position and forming an outlet port adjacent the outer end, and a valve in the housing movable between an open position permitting fluid flow into the valve guide toward the outlet end and a closed position preventing such flow. A valve piston in the valve guide and axially fixed in the valve housing is engaged in the front position of the valve guide with the port to block flow through same. A fitting sleeve surrounding and axially shiftable on the valve housing has at the outer end an end fitting complementary to the tank filler neck. | 08-04-2011 |
20110277880 | FUEL PUMP NOZZLE - The subject matter of the invention is a fuel pump nozzle, with an inlet ( | 11-17-2011 |
20120073700 | FUEL PUMP NOZZLE - The invention relates to a main valve for a fuel pump nozzle the main valve comprising a shut-off body for closing a fuel line and a displacement space that is configured to avoid undesirable pressure surges during closing of the main valve. The invention further relates to a fuel pump nozzle comprising a main valve according to the invention. | 03-29-2012 |
20140048173 | FUEL NOZZLE - The invention relates to a filling nozzle for dispensing liquid into a tank of a motor vehicle, having an actuating lever for a valve device and having a safety device moveable from a blocking position into an enabling position, wherein, in the blocking position, the valve device is closed regardless of the position of the actuating lever, and in the enabling position, the valve device can be opened by means of the actuating lever. The operative connection between the safety device and valve device is realized without external energy. The invention makes it possible to realize a misfilling inhibitor without external electrical energy, for example, and thus to fit a filling nozzle for urea solution, for example, in the explosion-protected region of a conventional fuel filling pump. | 02-20-2014 |
20140097610 | BREAKAWAY COUPLING FOR A LIQUID LINE - The invention relates to a breakaway coupling for a liquid line comprising a first and a second coupling part ( | 04-10-2014 |
20140319145 | Annularly closable band and use thereof - The invention relates to an annularly closable band for encircling one or more articles, having an inner side, which is intended to face the article or articles to be encircled, an outer side located opposite the inner side, and two end regions ( | 10-30-2014 |
20150091295 | Nut, socket and adapter for a fluid nozzle - The invention relates to a nut ( | 04-02-2015 |
Patent application number | Description | Published |
20080281281 | Vacuum Therapy Device - The invention relates to a therapeutic device to promote the healing of a wound, comprising a porous paid which is permeable for fluids to place on the wound, a bandage to cover the wound and to provide an essentially airtight seal around the wound, a drainage line connecting the pad with a suction pump so that suction can be applied to the wound to draw the fluids away from it, whereby the line is connected to the suction pump via a canister to collect fluid sucked from the wound, a connector to connect the pad to the drainage line, means to determine a prevailing wound pressure basically comprising the wound and this surrounding skin area, as well as a control unit to control the wound pressure. In order to generally improve metrology with the goal of making possible a more reliable and more secure dressing of the wound, and also to design metrology in an especially simple and error-free way, it is proposed that the pad interconnect the suction pump solely via the drainage line. | 11-13-2008 |
20100063464 | Tube Connector for a Vacuum Therapy Device - The invention relates to a therapeutic device to promote the healing of a wound, comprising a cover around the wound to form an essentially airtight cover over the wound, whereby a liquid-permeable pad is preferably provided between the wound and cover, a drainage line connecting the cover with a suction pump so that the wound can be suctioned to draw the fluids from it, and a connector to connect the cover with the drainage line, whereby the connector is provided with an opening to connect the proximal end of the drainage line to the wound, with which a more solid connection is guaranteed between the cover and the drainage line, which however at the same time has sufficient elasticity to conform to the respective body form and/or shape of the wound. It is also proposed that the connection contain fastening sections which extend from an area radiating from the opening to the area near the outer edge of the cover and which are separated from each other by notches. | 03-11-2010 |
Patent application number | Description | Published |
20150064389 | WINDOW PANEL FOR AN AIRFRAME AND METHOD OF PRODUCING SAME - The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core. | 03-05-2015 |
20150118001 | SYSTEM AND METHOD OF MANUFACTURING COMPOSITE MODULES - A system for producing a fibre-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fibre layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a moulding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station. | 04-30-2015 |