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A microwave oven adapted for use within a motor vehicle dashboard area. The microwave oven has a removable storage cassette, and slidable platforms for securing and serving containers of beverages and foods.
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| Number | Title | Issue Date |
| 8141365 | Plunged hole arrangement for annular rich-quench-lean gas turbine combustors A combustor may include an outer liner having a first row and a second row of circumferentially distributed air admission holes. The second row of the outer liner may be downstream of the first row of the outer liner, and the air admission holes of the first row of ... | 03/27/2012 |
| 8127554 | Quench jet arrangement for annular rich-quench-lean gas turbine combustors An outer liner of a combustor of a gas turbine engine includes a plurality of liner regions arranged adjacent one another and separated by boundary lines; and a plurality of air admission holes formed in the liner regions. The air admission holes within each liner r... | 03/06/2012 |
| 7984615 | Combustors for use in turbine engine assemblies An engine assembly includes a scroll assembly including an inlet, an outlet, an inner section, and an outer section. Each of the inner section and the outer section extend between the inlet and the outlet with the outer section being longer than the inner section. T... | 07/26/2011 |
| 7942006 | Combustors and combustion systems for gas turbine engines A combustion system includes a combustor having a forward annular liner having a first plurality of effusion holes, and an aft annular liner having a second plurality of effusion holes and forming a combustion chamber with the forward annular liner. The first plural... | 05/17/2011 |
| 7942007 | Heat shield element for lining a combustion chamber wall, combustion chamber and gas turbine The invention relates to a heat shield element for lining a combustion chamber wall, to a combustion chamber and to a gas turbine. The heat shield element comprises a hot side that can be exposed to a hot medium, a wall side opposite said hot side, and a peripheral ... | 05/17/2011 |
| 7926284 | Quench jet arrangement for annular rich-quench-lean gas turbine combustors A combustor includes an outer liner having a first row and a second row of circumferentially distributed air admission holes penetrating therethrough. The combustor further includes an inner liner circumscribed by the outer liner and having a first row and a second ... | 04/19/2011 |
| 7891194 | Configuration of dilution openings in a turbomachine combustion chamber wall An annular combustion chamber of a turbomachine is provided. The combustion chamber includes an end wall provided at an upstream end of the chamber and side walls extending longitudinally from the end wall to an orifice for discharging a stream of combustion gases p... | 02/22/2011 |
| 7874159 | Gas turbine combustion chamber wall with dampening effect on combustion chamber vibrations A gas turbine combustion chamber wall has an outer wall skin and an inner wall skin, with the outer wall skin (9) and the inner wall skin (10) being arranged essentially parallel to each other and spaced apart from each other by a gap (14). The ... | 01/25/2011 |
| 7793503 | Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine The invention relates to a heat shield block, particularly for lining a combustion chamber wall, with a hot side that can be subjected to the action of hot medium and with a wall side situated opposite the hot side. A core area, which has a core material, extends in... | 09/14/2010 |
| 7748222 | Performance of a combustion chamber by multiple wall perforations An annular wall for the combustion chamber of a turbomachine has a cold side and a hot side, said wall being provided with a plurality of primary holes and a plurality of dilution holes distributed in circumferential rows, together with a plurality of cooling orific... | 07/06/2010 |
| 7726131 | Floatwall dilution hole cooling A combustor for a gas turbine engine is provided, the combustor having an outer shell with an outer surface exposed to cooling air and an inner surface, and at least one floatwall panel attached to the inner surface of the outer shell and having a trailing edge. At ... | 06/01/2010 |
| 7658076 | Open cooled component for a gas turbine, combustion chamber, and gas turbine The invention relates to an open-cooled component for a gas turbine having an outer wall which is subjected to hot gas and which at least partly defines a first cavity for a first medium and in which through-openings are arranged, which through-openings open into th... | 02/09/2010 |
| 7631502 | Local cooling hole pattern A combustor assembly includes an inner and an outer liner defining a combustion chamber. The inner and outer liner includes a plurality of cooling holes that are spaced a specified distance apart. The cooling holes include a specified inclination angle and circumfer... | 12/15/2009 |
| 7624578 | Method and apparatus for generating combustion products within a gas turbine engine A method for generating combustion products within a gas turbine engine includes directing an internal air/fuel mixture towards a stagnation point in close proximity to an inner surface of a porous wall defining a combustion chamber. The internal air/fuel mixture is... | 12/01/2009 |
| 7614235 | Combustor cooling hole pattern A combustor assembly includes an inner and outer liner defining a combustion chamber. The inner and outer liners include a plurality of cooling holes spaced a specified distance apart. The cooling holes include first, second and third groups. The first group of cool... | 11/10/2009 |
| 7546737 | Segmented effusion cooled gas turbine engine combustor A combustor includes two or more sets of effusion cooling holes that extend through the inner and outer liners. Each set of effusion cooling holes includes one or more initial rows of effusion cooling holes, one or more final rows of effusion cooling holes disposed ... | 06/16/2009 |
| 7509809 | Gas turbine engine combustor with improved cooling A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in fuel nozzle regions than in other areas of the combustor liner. ... | 03/31/2009 |
| 7506512 | Advanced effusion cooling schemes for combustor domes A cooling scheme for a dome comprises an effusion array drilled directly through a single walled dome. In one embodiment, the layout of the holes comprises two regions, a region close to the fuel injector where the holes follow a tangential path around the injector,... | 03/24/2009 |
| 7464554 | Gas turbine combustor heat shield panel or exhaust panel including a cooling device A combustor heat shield panel has interior and exterior surfaces with a number of circuitous non-interconnected cooling gas passageways having inlets on the exterior surface and outlets on the interior surface. ... | 12/16/2008 |
| 7373772 | Turbine combustor transition piece having dilution holes A transition piece body, having an inlet end for receiving combustion products from a turbine combustor and an outlet end for flowing the gaseous products into a first stage nozzle, has dilution holes in zones respectively adjacent the transition piece body inlet an... | 05/20/2008 |
| 7363763 | Combustor A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a ... | 04/29/2008 |
| 7308794 | Combustor and method of improving manufacturing accuracy thereof An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor... | 12/18/2007 |
| 7302801 | Lean-staged pyrospin combustor A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a pr... | 12/04/2007 |
| 7278256 | Pulsed combustion engine A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to th... | 10/09/2007 |
| 7269958 | Combustor exit duct A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions. ... | 09/18/2007 |
| 7260936 | Combustor having means for directing air into the combustion chamber in a spiral pattern A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral patter... | 08/28/2007 |
| 7219498 | Waffled impingement effusion method A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal s... | 05/22/2007 |
| 7216485 | Adjusting airflow in turbine component by depositing overlay metallic coating A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes ar... | 05/15/2007 |
| 7204089 | Arrangement for the cooling of thermally highly loaded components An inexpensively manufacturable arrangement for the cooling of thermally highly loaded components, for example the combustion chamber of a gas turbine, comprises cavities (4) provided on the thermally loaded inner surface/air exit side (3) of the wall ... | 04/17/2007 |
| 7186091 | Methods and apparatus for cooling gas turbine engine components A method of cooling a gas turbine engine component having a perforate metal wall includes providing a plurality of pores in the wall, wherein the pores extend substantially perpendicularly through the wall, and wherein the pores are covered and sealed closed at firs... | 03/06/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7146816 | Effusion momentum control A combustor liner for shielding an engine from heat generated in a combustion zone includes a sheet with a cool surface for intercepting a cooling air stream and a hot surface enclosing the combustion zone, the combustor liner further including an array of effusion ... | 12/12/2006 |
| 7140185 | Heatshielded article A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated co... | 11/28/2006 |
| 7124588 | Combustion chamber of gas turbine with starter film cooling A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumfere... | 10/24/2006 |
| 7121096 | Gas turbine engine combustor A combustor for a gas turbine engine comprising a combustion chamber wall having formed therein at least one hole for admitting air into the combustion chamber and at least one air intake chute aligned with said hole. The air intake chutes are attached to the combus... | 10/17/2006 |
| 7104067 | Combustor liner with inverted turbulators A combustor liner for a gas turbine, the combustor liner having a substantially cylindrical shape; and a plurality of axially spaced circumferential grooves formed in an outside surface of the combustor liner. ... | 09/12/2006 |
| 7104065 | Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surfac... | 09/12/2006 |
| 7096668 | Cooling and sealing design for a gas turbine combustion system An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received... | 08/29/2006 |
| 7093441 | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion of the combustor interior volume converges from fore ... | 08/22/2006 |
| 7093439 | Heat shield panels for use in a combustor for a gas turbine engine The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plu... | 08/22/2006 |
