Abstract: A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Abstract: Provided is a locking mechanism for a ski-binding, the locking mechanism comprising only one lever adapted to be pivoted between an engaged and a disengaged position. The lever further comprises at least one lug, the at least one lug adapted to engage with a notch formed in a mounting plate in an engaged position, and wherein the lug is adapted to hold the lever in a non-sliding manner when engaged with the notch. Explicitly, the locking mechanism does not comprise a second lever. Also provided is a ski-binding comprising only one locking mechanism, or adapted to receiving only one locking mechanism, and a mounting plate for use with the locking mechanism, and ski-binding.

Abstract: Provided is a locking mechanism for a ski-binding, the locking mechanism comprising only one lever adapted to be pivoted between an engaged and a disengaged position. The lever further comprises at least one lug, the at least one lug adapted to engage with a notch formed in a mounting plate in an engaged position, and wherein the lug is adapted to hold the lever in a non-sliding manner when engaged with the notch. Explicitly, the locking mechanism does not comprise a second lever. Also provided is a ski-binding comprising only one locking mechanism, or adapted to receiving only one locking mechanism, and a mounting plate for use with the locking mechanism, and ski-binding.

Abstract: A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Abstract: Provided is a locking mechanism for a ski-binding, the locking mechanism comprising only one lever adapted to be pivoted between an engaged and a disengaged position. The lever further comprises at least one lug, the at least one lug adapted to engage with a notch formed in a mounting plate in an engaged position, and wherein the lug is adapted to hold the lever in a non-sliding manner when engaged with the notch. Explicitly, the locking mechanism does not comprise a second lever. Also provided is a ski-binding comprising only one locking mechanism, or adapted to receiving only one locking mechanism, and a mounting plate for use with the locking mechanism, and ski-binding.

Abstract: A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Abstract: A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Abstract: Two concentric, partially overlapping annular plates mounted on a parallel support plate are provided for partly defining the gas flow path and for shielding bearings, etc. from hot combustion gases in a radial flow gas turbine. The radially outer plate is cooled by compressed air channeled past the plate surface opposite the combustion gases. The compressed air is metered to achieve a temperature distribution decreasing in the radially inward direction for providing sealing contact between the outer edge and the support plate. The radially inner plate is cooled by film cooling using the compressed air exiting the outer plate channel in the vicinity of the overlap.