Abstract: Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.

Abstract: A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.

Abstract: Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.

Abstract: A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.

Abstract: A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.

Abstract: A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.

Abstract: A seal in a turbine engine for preventing axial leakage through a radial gap between a stationary structure and a rotating structure, wherein the radial gap is defined by an inner radial surface that opposes an outer radial surface across the radial gap, the seal including: a first groove disposed on one of the inner radial surface and the outer radial surface; and a first tooth that projects radially from the other of the inner radial surface and the outer radial surface; wherein the first groove, at an upstream end, comprises a gradual slope that slopes away from the surface on which the first tooth is located and, at a downstream end, comprises a steep slope; and wherein the first tooth comprises an axial position that is approximately just upstream of the axial position of the upstream end of the groove.