Patent application number | Description | Published |
20100183435 | Gas Turbine Vane Platform Element - A gas turbine CMC shroud plate ( | 07-22-2010 |
20100284798 | Turbine Airfoil With Dual Wall Formed from Inner and Outer Layers Separated by a Compliant Structure - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer. | 11-11-2010 |
20100284822 | Turbine Airfoil with a Compliant Outer Wall - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation in the outer layer is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a support structure. The outer layer may be a compliant layer configured such that the outer layer may thermally expand and thereby reduce the stress within the outer layer. The outer layer may be formed from a nonplanar surface configured to thermally expand. In another embodiment, the outer layer may be planar and include a plurality of slots enabling unrestricted thermal expansion in a direction aligned with the outer layer. | 11-11-2010 |
20110110762 | Damping Element for Reducing the Vibration of an Airfoil - An airfoil ( | 05-12-2011 |
20110142639 | MODULAR TURBINE AIRFOIL AND PLATFORM ASSEMBLY WITH INDEPENDENT ROOT TEETH - A turbine airfoil ( | 06-16-2011 |
20110142684 | Turbine Engine Airfoil and Platform Assembly - A turbine airfoil ( | 06-16-2011 |
20110194943 | COOLED SNUBBER STRUCTURE FOR TURBINE BLADES - A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade. | 08-11-2011 |
20110236221 | Four-Wall Turbine Airfoil with Thermal Strain Control for Reduced Cycle Fatigue - A turbine airfoil ( | 09-29-2011 |
20110243724 | TURBINE AIRFOIL TO SHROUND ATTACHMENT - A turbine airfoil ( | 10-06-2011 |
20110297344 | TURBINE AIRFOIL TO SHROUD ATTACHMENT METHOD - Bi-casting a platform ( | 12-08-2011 |
20120237358 | TURBINE BLADE TIP - A tip rail configured to reduce stress when formed from a single crystal alloy is disclosed. The tip rail may be formed from at least one single crystal alloy oriented in a low modulus direction such that a gap exists at a location where the axis of orientation is positioned at a 45 degree angle to the outer surface of the suction side to reduce stress on the tip rail. The tip rail may be separately formed from a generally elongated blade to which the tip rail is configured to be attached. The tip rail may form a leading edge region recess proximate to the leading edge between an inner edge of the tip rail on the suction side and an inner edge of the tip rail on the pressure side and may form a trailing edge region recess proximate to the trailing edge. The gap reduces stress during use operation of a gas turbine engine in which the tip rail is attached to a turbine airfoil. | 09-20-2012 |
20130064667 | TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT - Platforms ( | 03-14-2013 |
20130294913 | TURBINE BLADE WITH TUNED DAMPING STRUCTURE - A turbine blade is provided comprising: a root; an airfoil comprising an external wall extending radially from the root and having a radially outermost portion; and a damping structure. The external wall may comprise first and second side walls joined together to define an inner cavity of the airfoil. The damping structure may be positioned within the airfoil inner cavity and coupled to the airfoil so as to define a tuned mass damper. | 11-07-2013 |