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Morgan, SC
Douglas C. Morgan, Moore, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20100168980 | OPERATING A TURBINE AT BASELOAD ON COLD FUEL WITH HOT FUEL COMBUSTION HARDWARE - A method and algorithm are provided to operate a gas turbine at baseload in an emission compliant capable mode to avoid combustion dynamics while operating with cold fuel and hot fuel combustion hardware. The method includes performing a gas turbine operational sequence such as a startup to an emission compliant capable mode. A gas fuel temperature is measured. The gas turbine is operated in the emissions compliant capable mode according to a designated fuel split for avoiding combustion dynamics when a temperature for a gas fuel is below a designated value. A determination is made whether a modified wobbe index for the gas fuel is below an emissions compliant value. An alarm is activated if the modified wobbe index is below the emissions compliant value to notify the operator of a potential emissions shift. | 07-01-2010 |
Rex A. Morgan, Simpsonville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20090158734 | METHOD FOR ADJUSTING THE OPERATION OF A TURBOMACHINE RECEIVING A RECIRCULATED EXHAUST GAS - A method for adjusting the operation of a turbomachine integrated with an exhaust gas recirculation (EGR) system is provided. The method may utilize the composition of an inlet fluid entering the turbomachine. The method may also utilize a variety of turbomachine operating data. | 06-25-2009 |
Rex Allen Morgan, Simpsonville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20100080685 | Method and Apparatus for Gas Turbine Engine Temperature Management - A cooling system for a turbine engine, as well as a methodology for controlling the cooling system, is described. A valve member is disposed between a cooling fluid passage and a wheel space of the turbine engine and operates to admit cooling fluid to the wheel space for cooling thereof. The valve assembly is responsive to a condition in the wheel space and varies the flow of additional cooling fluid to the wheel space based on that condition. | 04-01-2010 |
Stephen Morgan, Columbia, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20110090342 | MULTI-MODE IMAGING IN THE THERMAL INFRARED FOR CHEMICAL CONTRAST ENHANCEMENT - A system and method for analyzing a sample is disclosed. At least a portion of the sample is illuminated with modulated light from a light source, such as an infrared light source. Infrared energy from the sample is monitored with an infrared detector as the sample is being illuminated with the modulated light. The AC response of the infrared energy is analyzed to determine at least one of emission data or reflection data about the sample. The emission data or the reflection data can be used to enhance chemical contrast between varying substances on the sample. | 04-21-2011 |
Stephen L. Morgan, Columbia, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20090250613 | Chemically-Selective Detector and Methods Relating Thereto - In accordance with certain embodiments of the present disclosure, a method for adjusting the spectral detectivity of a thermal detector is described. The method includes coating the light sensitive portion of a thermal detector with a first material to reduce the response of the detector. The first material is coated with a second material that is thermally thin and has spectral absorption characteristics. The second material is coated with a third material that is thermally thick, whereby the spectral absorbance of the second material as filtered by the third material primarily determines the thermal conversion of the thermal detector. | 10-08-2009 |
Victor Morgan, Greenville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20100247329 | TURBINE BLADE ASSEMBLIES WITH THERMAL INSULATION - A turbine blade assembly for a gas turbine includes a spar with raised ribs, a spacer with a plurality of protrusions mounted around the spar, and an outer shell mounted around the spacer. The protruding portions on the spacer surround the raised ribs on the spar. The protruding portions of the spacer act to space the interior surfaces of the outer shell away from the spar to provide a thermal insulation layer of cooling air. | 09-30-2010 |
Victor Morgan, Simpsonville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20080298956 | Shroud configuration having sloped seal - A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner shrouds being respectively engaged with the leading and trailing edge grooves of the outer shroud so as to axially and radially lock the inner shrouds to the outer shrouds. At least one of the trailing edge hook of the inner shroud and the trailing edge groove of the outer shroud includes a sloped surface disposed at an angle to an axial direction of the rotor and to a radial direction of the rotor and facing the other of the inner and outer shrouds whereby a radial inward force on the inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between the inner and outer shrouds. | 12-04-2008 |
Victor John Morgan, Simpsonville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20100072710 | Gas Turbine Seal - A seal is provided for sealing two adjacent components of a gas turbine engine. The seal has first and second sealing surfaces that operate to seal the adjacent components to create an effective seal therebetween. Additionally, the seal has a first end and a second end, with the second end having a necked down portion, which is configured to internally engage the first end in a sliding, overlapping manner. | 03-25-2010 |
| 20100247300 | REDUCING INTER-SEAL GAP IN GAS TURBINE - A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into the first slot and a first adjacent slot on the second arcuate component; a second seal disposed into the second slot and a second adjacent slot on the second arcuate component, leaving a gap between the first seal and the second seal; and a connector coupled to the first seal and the second seal and substantially covering the gap between the first seal and the second seal. | 09-30-2010 |
Victor John Morgan, Greenville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20110110771 | AIRFOIL HEAT SHIELD - Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil. | 05-12-2011 |
| 20110110790 | HEAT SHIELD - A heat shield is disclosed. The heat shield may include a base layer and a spacer layer. The spacer layer may be coupled to the base layer. The spacer layer may define a plurality of flow channels. The base layer and the spacer layer may be configured to associate with a hot gas path component. | 05-12-2011 |