| 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 |
| 20090087312 | Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method - A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss. | 04-02-2009 |
| 20090246011 | FILM COOLING OF TURBINE COMPONENTS - A turbine component includes a flow path surface and a trench disposed in the flow path surface. At least one cooling through hole is located in the trench and is capable of injecting a cooling flow onto the flow path surface of the turbine component. The cooling flow forms a cooling film on the flow path surface. A method of cooling a turbine component includes injecting a cooling flow onto a flow path surface of the turbine component through at least one cooling through hole disposed in a trench in the turbine component. A cooling film is formed by the cooling flow between the flow path surface and a hot gas flow. | 10-01-2009 |
| 20100054954 | TURBINE BUCKET FOR A TURBOMACHINE AND METHOD OF REDUCING BOW WAVE EFFECTS AT A TURBINE BUCKET - A turbine bucket for a turbomachine includes a main body portion having a base portion and an airfoil portion, the base portion includes a bucket cavity forward region and a shank cavity. The turbine bucket also includes a cooling channel that extends through the main body portion. At least one flow passage extends between one of the cooling channel and the shank cavity, toward the bucket cavity forward region. The at least one flow passage delivers a flow of cooling gas toward the bucket cavity forward region. The flow of cooling gas limits ingestion of hot gases into the bucket cavity forward region. | 03-04-2010 |
| 20100178159 | Turbine Bucket Angel Wing Compression Seal - The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon. | 07-15-2010 |
| 20100284800 | TURBINE NOZZLE WITH SIDEWALL COOLING PLENUM - A turbine nozzle segment includes an outer band portion, an inner band portion, and at least one nozzle vane extending between the band portions. A cooling plenum is defined in a mating side face of at least one of the band portions and extends transversely at least partially through the respective band portion. First and second cooling passages extend from the cooling plenum to respective first and second cooling chambers. | 11-11-2010 |
| 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 |
