Abstract: An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the rotational speed of the air leaving the stator and entering the interior of the rotor.

Abstract: An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the rotational speed of the air leaving the stator and entering the interior of the rotor.

Abstract: An apparatus for improving heat transfer through a leading portion of an aircraft engine. The apparatus includes an annular channel that is defined by the leading portion. A source for gas that is fluidly connected to the channel and a narrow region that is defined within the annular channel.

Abstract: In accordance with an embodiment, described herein is a system and method for provisioning cloud services across heterogeneous computing environments. A plurality of provisioning instructions stored on a configuration management server can be partitioned into a plurality of ranges. A plurality of client nodes connected to the configuration management server can be configured into a plurality of groups, each group providing one or more computing environments on one or more virtual machines for hosting a cloud service. Each computing environment in a particular group can be associated with a provisioning instruction launcher that specifies a particular range of provisioning instructions. When a virtual machine in a particular group reboots, the computing environment on the virtual machine searches for the latest provisioning instruction in the range corresponding to the particular group.

Abstract: An aircraft anti-icing system includes an inlet lip that includes an outer shell attached to a bulkhead. The inlet lip encloses an annular housing volume. The system further includes one or more vanes extending from the bulkhead into the annular housing volume. Each vane of the one or more vanes includes a first end coupled to the bulkhead, a free end extending into the annular housing volume, and a vane body extending therebetween. The one or more vanes are positioned downstream from a nozzle configured to direct a high temperature gas stream into the annular housing volume in a first direction. The one or more vanes are configured to redirect the high temperature gas stream through a first turn angle from the first direction to a second direction. The second direction is configured to reduce a direct impingement of the high temperature gas stream on an inner surface of the inlet lip.

Abstract: An apparatus for improving heat transfer through a leading portion of an aircraft engine. The apparatus includes an annular channel that is defined by the leading portion. A source for gas that is fluidly connected to the channel and a narrow region that is defined within the annular channel.

Abstract: An aircraft anti-icing system includes an inlet lip that includes an outer shell attached to a bulkhead. The inlet lip encloses an annular housing volume. The system further includes one or more vanes extending from the bulkhead into the annular housing volume. Each vane of the one or more vanes includes a first end coupled to the bulkhead, a free end extending into the annular housing volume, and a vane body extending therebetween. The one or more vanes are positioned downstream from a nozzle configured to direct a high temperature gas stream into the annular housing volume in a first direction. The one or more vanes are configured to redirect the high temperature gas stream through a first turn angle from the first direction to a second direction. The second direction is configured to reduce a direct impingement of the high temperature gas stream on an inner surface of the inlet lip.

Abstract: In accordance with an embodiment, described herein is a system and method for provisioning cloud services across heterogeneous computing environments. A plurality of provisioning instructions stored on a configuration management server can be partitioned into a plurality of ranges. A plurality of client nodes connected to the configuration management server can be configured into a plurality of groups, each group providing one or more computing environments on one or more virtual machines for hosting a cloud service. Each computing environment in a particular group can be associated with a provisioning instruction launcher that specifies a particular range of provisioning instructions. When a virtual machine in a particular group reboots, the computing environment on the virtual machine searches for the latest provisioning instruction in the range corresponding to the particular group.