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A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall f

A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.

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1. A component for a turbine engine, said component comprising: a substrate comprising a substrate first surface, said substrate first surface comprising a recess defined therein;an insert coupled to said substrate proximate said substrate first surface, wherein said insert is shaped complementary t

1. A component for a turbine engine, said component comprising: a substrate comprising a substrate first surface, said substrate first surface comprising a recess defined therein;an insert coupled to said substrate proximate said substrate first surface, wherein said insert is shaped complementary to a shape of said recess;a channel defined by a first channel wall formed in said substrate and a second channel wall formed by at least one coating disposed on said substrate first surface;an inlet opening defined in flow communication with said channel, said inlet opening defined by a first inlet wall formed in said substrate and a second inlet wall defined by said insert; anda transition region between said channel and said inlet opening such that said transition region is in flow communication with said channel and is at least partially defined by a first transition wall formed in said substrate and a second transition wall formed by said insert. 2. The component of claim 1, wherein a longitudinal axis of said inlet opening intersects a longitudinal axis of said channel at an angle that is obtuse. 3. The component of claim 1, wherein said insert comprises a plug disposed in said inlet opening proximate said substrate first surface. 4. The component of claim 1, wherein a depth of said transition region decreases between said inlet opening and said channel. 5. A turbine engine comprising: a combustor section configured to generate a hot gas; anda component disposed along a path configured to be traversed by the hot gas, said component comprising: a substrate comprising a substrate first surface, said substrate first surface comprising a recess defined therein;an insert coupled to said substrate proximate said substrate first surface, wherein said insert is shaped complementary to a shape of said recess;a channel defined by a first channel wall formed in said substrate and a second channel wall formed by at least one coating disposed on said substrate first surface;an inlet opening defined in flow communication with said channel, said inlet opening defined by a first inlet wall formed in said substrate and a second inlet wall defined by said insert; anda transition region disposed between said channel and said inlet opening such that said transition region is in flow communication with said channel and is at least partially defined by a first transition wall formed in said substrate and a second transition wall formed by said insert. 6. The turbine engine of claim 5, wherein a longitudinal axis of said inlet opening intersects a longitudinal axis of said channel at an angle that is obtuse. 7. The turbine engine of claim 5, wherein said insert comprises a plug disposed in said inlet opening proximate said substrate first surface. 8. The turbine engine of claim 5, wherein a depth of said transition region decreases between said inlet opening and said channel. 9. A method of forming a component for a turbine engine, said method comprising: forming a first channel wall of a channel in a substrate;forming a first inlet wall of an inlet opening in the substrate;forming a recess in the substrate first surface;coupling an insert to the substrate proximate a first surface of the substrate, wherein the insert defines a second inlet wall of the inlet opening, and wherein the insert is shaped complementary to a shape of the recess;disposing at least one coating on the substrate first surface, wherein the at least one coating forms a second channel wall of the channel, the inlet opening defined in flow communication with the channel; andforming a transition region between the channel and the inlet opening such that the transition region is in flow communication with the channel and is at least partially defined by a first transition wall formed in the substrate and a second transition wall formed by the insert. 10. The method of claim 9, further comprising forming the first inlet wall such that a longitudinal axis of the inlet opening intersects a longitudinal axis of the channel at an angle that is obtuse. 11. The method of claim 9, wherein said coupling the insert to the substrate comprises disposing a plug in the inlet opening proximate the substrate first surface. 12. The method of claim 9, further comprising forming the transition region such that a depth of the transition region decreases between the inlet opening and the channel.