Abstract: A method for forming a hole in an object is provided. The method includes forming a starter hole in the object, providing an electrochemical machining electrode that includes insulation that extends only partially around the electrode, and inserting the electrode into the starter hole to form a hole in the object that has an inlet defined by a first cross-sectional area and an outlet defined by a second cross-sectional area.

Abstract: A method for forming holes in an object is provided. The method includes providing an electrochemical machining (ECM) electrode including a first section having insulation that circumscribes the first section, and a second section having insulation that extends only partially around the second section. The method also includes inserting the electrode into the object, such that in a single pass the electrode forms a hole that includes a first portion having a first cross-sectional area and a second portion having a second cross-sectional area.

Abstract: Methods for optimizing at least one operating parameter of an engine component using an experimentally measured 3D flow field involving providing a magnetic resonance imaging machine, providing a model of an engine component, placing the model into the magnetic resonance imaging machine with a fluid flow source for applying an external fluid flow, applying the external fluid flow to the model, collecting data related to the external fluid flow about the model, and optimizing at least one operating parameter of the component using the data.

Abstract: Methods for optimizing at least one operating parameter of an engine component using an experimentally measured 3D flow field involving providing a magnetic resonance imaging machine, providing a model of an engine component, placing the model into the magnetic resonance imaging machine with a fluid flow source for applying an external fluid flow, applying the external fluid flow to the model, collecting data related to the external fluid flow about the model, and optimizing at least one operating parameter of the component using the data.

Abstract: A method for forming holes in an object is provided. The method includes forming a starter hole in the object, providing an electrochemical machining electrode having at least one insulated section that substantially circumscribes the electrode and at least one uninsulated section, and inserting the electrode into the starter hole to facilitate forming a hole defined by at least one first section having a first cross-sectional area and at least one second section having a second cross-sectional area.

Abstract: A method for forming a hole in an object is provided. The method includes forming a starter hole in the object, providing an electrochemical machining electrode that includes insulation that extends only partially around the electrode, and inserting the electrode into the starter hole to form a hole in the object that has an inlet defined by a first cross-sectional area and an outlet defined by a second cross-sectional area.

Abstract: A method for forming holes in an object is provided. The method includes providing an electrochemical machining (ECM) electrode including a first section having insulation that circumscribes the first section, and a second section having insulation that extends only partially around the second section. The method also includes inserting the electrode into the object, such that in a single pass the electrode forms a hole that includes a first portion having a first cross-sectional area and a second portion having a second cross-sectional area.

Abstract: A method for assembling a turbine engine assembly is provided. The turbine engine includes a core engine. The method includes coupling a first rotor spool within the engine assembly wherein the first rotor spool includes a first shaft. The method further includes coupling a second rotor spool within the engine assembly wherein the second rotor spool includes a second shaft. The method also includes coupling a third rotor spool within the engine assembly wherein the third rotor spool includes a third shaft. At least one of the first, second, and third shafts include a first end, an opposing second end, and a tubular portion extending between the first and second ends. A reinforcing layer circumscribes a portion of the tubular portion wherein at least a portion of the reinforcing layer is a metallic matrix composite (MMC) material that includes reinforcing fibers. A turbine engine is also provided.

Abstract: An article including a body terminating in an end portion, for example an airfoil of a blade terminating in an airfoil tip, comprises an end or tip barrier discrete from and bonded with the body. The barrier is substantially impregnable to penetration of liquid, for example water vapor. In a form in which the body is laminated, the barrier is a non-directionally dependent material, resisting delamination. In one form of a method for making such article, the end portion of an existing article is trimmed back to provide a body preform, and an end barrier is bonded with the body preform. In another method form, an end barrier is bonded with a provided body preform, the barrier and body preform together defining the article. Such articles are repairable by removing and replacing a damaged end portion or damaged barrier.