| Patent application number | Description | Published |
|---|
| 20090272122 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. | 11-05-2009 |
| 20090287458 | BROACH TOOL DESIGN METHODOLOGY AND SYSTEMS - This disclosure relates to a design methodology used in manufacturing a broaching tool for cutting slots in aerospace disk applications. The method includes modeling geometry of the slot and the broach tool, which is based upon an initial minimum tooth rise that is determined empirically for the particular disk material. The number of broach inserts and teeth per insert is calculated, and the broach inserts are modeled. The stresses and deformation of the lug are calculated in a finite elements environment based upon simulated incremental broach tool movements. If the lug is not within specifications based upon design constraints, then the broach tool is revised and the simulations are repeated until the slot is within the desired specifications. | 11-19-2009 |
| 20100104433 | CERAMIC SHROUD ASSEMBLY - A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring. | 04-29-2010 |
| 20100170264 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. | 07-08-2010 |
| 20100257864 | REVERSE FLOW CERAMIC MATRIX COMPOSITE COMBUSTOR - A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite. | 10-14-2010 |
| Patent application number | Description | Published |
|---|
| 20090276136 | METHOD FOR CALCULATING CONFIDENCE ON PREDICTION IN FAULT DIAGNOSIS SYSTEMS - A method and system is developed that provides a confidence measure of a prediction of a fault in a gas turbine engine. The confidence measure is developed based upon evaluating the results of a plurality of past predictions and comparing them to an actual fault. | 11-05-2009 |
| 20100017092 | HYBRID FAULT ISOLATION SYSTEM UTILIZING BOTH MODEL-BASED AND EMPIRICAL COMPONENTS - A method of operating and a fault diagnosis system compares readings to predicted faults using a model-based component, and a database of previous actual fault examples. A predicted fault is provided to an output based upon a combination of both the model-based component and the actual fault examples. | 01-21-2010 |
| 20110153295 | METHOD AND SYSTEM FOR MODELING THE PERFORMANCE OF A GAS TURBINE ENGINE - A method for modeling the performance of a gas turbine engine is provided. The method includes the steps of: 1) providing a processor; 2) inputting flight condition parameter data and engine output parameter data into a gas turbine engine model operating on the processor, which model includes a physics-based engine model that uses the flight condition parameter data to produce estimated engine output parameter data, and determines residuals from the engine output parameter data and the estimated engine output parameter data; 3) partitioning the flight condition parameter data and residuals into training data and testing data; 4) performing a correlation reduction on the training data, which analysis produces correlation adjusted training data; 5) performing an orientation reduction on the correlation adjusted training data, which reduction produces orientation adjusted training data; 6) reviewing the orientation adjusted training data relative to at least one predetermined criteria, and iteratively repeating the steps of performing a correlation reduction and an orientation reduction using the orientation adjusted training data if the criteria is not satisfied, and if the criteria is satisfied outputting the orientation adjusted training data; 7) producing estimated corrections to the orientation adjusted training data using one or more neural networks; 8) evaluating the neural adjusted data using the partitioned testing data; and 9) modeling the performance of the gas turbine using the estimated corrections to the orientation adjusted training data. | 06-23-2011 |
