Patent application number | Description | Published |
20090144156 | METHOD OF ADVERTISING - A retail establishment advertising system and method are disclosed. They allow a display of special content to interrupt a display of ongoing content on one or more display units. Ongoing content, such as advertisements, news, entertainment, or other relevant information, is provided on the display units until an urgent or security-related alert is required, and display of override content becomes necessary. Special content can include information relevant to specially discounted items or to security alert messages pertaining to, for example, security threats such as accidents, major delays, fire, missing children, terrorist activity, or other content deemed adequately pertinent to warrant interrupting the display of ongoing content. | 06-04-2009 |
20100199302 | DIGITAL COMMUNICATION SYSTEM WITH SECURITY FEATURES - A digital communication system is disclosed, that allows a display of override content to interrupt a display of ongoing content on one or more display units. Ongoing content, such as advertisements, news, entertainment, or other relevant information, is provided on the display units until an urgent or security-related alert is required, and display of override content becomes necessary. Override content can include information relevant to the security of a passenger or passer-by viewing the display. Override content can relate to security threats such as accidents, major delays, fire, missing children, terrorist activity, or other content deemed adequately pertinent to warrant interrupting the display of ongoing content. | 08-05-2010 |
Patent application number | Description | Published |
20080273970 | HP turbine vane airfoil profile - A two-stage high pressure turbine comprises a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 11-06-2008 |
20090116967 | COMPRESSOR TURBINE VANE AIRFOIL PROFILE - A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 05-07-2009 |
20090274558 | HP TURBINE BLADE AIRFOIL PROFILE - A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. | 11-05-2009 |
20100135813 | TURBINE BLADE FOR A GAS TURBINE ENGINE - The turbine blade comprises an airfoil having opposite pressure and suction sidewalls extending from a platform to a free end tip and in a chordwise direction from a leading edge to a trailing edge. The blade has two winglets extending in a chordwise direction from adjacent the leading edge to adjacent the trailing edge. Each winglet extends from the pressure sidewall upwardly and outwardly from the sidewall to provide a channel between them. Each winglet has a free end extending laterally beyond a surface defined by the pressure sidewall offset. | 06-03-2010 |
20100293958 | DESWIRLING EXHAUST MIXER - An exhaust mixer for a gas turbine engine including a plurality of circumferentially distributed alternating inner and outer lobes, where each of the inner lobes is configured with a circumferential offset between the base and the tip thereof, and a direction of the circumferential offset defined from the base to the tip of each of the inner lobes is the same for all of the inner lobes and opposite to that of a swirl component of a main gas path flow entering the exhaust mixer. | 11-25-2010 |
20150013341 | Exhaust Mixer with Offset Lobes - An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided. | 01-15-2015 |