An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.

Axial flow turbine

A turbomachine is provided and includes first and second endwalls disposed to define a pathway, each of the first and second endwalls including a surface facing the pathway and first and second blades extendible across the pathway from at least one of the first and second endwalls, each of the first and second blades having an airfoil shape and being disposed such that a pressure side of the first blade faces a suction side of the second blade. A portion of the surface of at least one of the first and second endwalls between the first and second blades has at least a first hump proximate to a leading edge and the pressure side of the first blade, and a second hump disposed at 10-60% of a chord length of the first blade and proximate to the pressure side thereof.

Turbine of a turbomachine

A transonic turbine blade. Expansion waves are generated by a lifting surface on the blade. The expansion waves extend downstream, through a shock generated at the trailing edge of an adjacent blade. The invention increases the strength of the shock, thereby attenuating the expansion waves passing through the shock. One stratagem for increasing the shock is to reduce the aerodynamic load of the trailing edge generating the shock.

Reduced shock transonic airfoil

An axial flow turbine includes in axial flow series a low pressure turbine section and a turbine exhaust system. The low pressure turbine section includes a final low pressure turbine stage having a circumferential row of static aerofoil blades followed in axial succession by a circumferential row of rotating aerofoil blades. Each aerofoil blade has a radially inner hub region and a radially outer tip region. The K value, being equal to the ratio of the throat dimension (t) to the pitch dimension (p), of each static aerofoil blade of the final low pressure turbine stage varies along the height of the static aerofoil blade, between the hub region and the tip region, according to a substantially W-shaped distribution.

PROBLEM TO BE SOLVED: To improve rigidity, damping characteristics, and vibration stress by using long blades. SOLUTION: The bucket has blades 118 of which length is about 45 inches or more. The bucket 102 includes a dovetail part 121 disposed close to a radially inward position of the bucket, a tip shroud disposed close to a radially outward position of the bucket, and an intermediate span shroud 610 disposed at a radially intermediate position between the radially inward position and outward position. The bucket 102 is formed of titanium base alloy comprising aluminum by about 2-6.25 wt.%, vanadium by about 3.5 wt.% or less, tin by about 2.25 wt.% or less, zirconium by about 2.25 wt.% or less, molybdenum by about 1.75-5.0 wt.%, chrome by about 2.25 wt.% or less, silicon by about 0.7 wt.% or less, iron by about 2.3 wt.% or less, and titanium for the rest. COPYRIGHT: (C)2009,JPO&INPIT

Low pressure section steam turbine bucket

A steam turbine that passes more turbine driving steam by off-setting the turbine moving blade throat•pitch ratio before operation and, when a blade untwist is generated during operation, causing more turbine driving steam to flow by maintaining an appropriate value, and, at the same time causing the turbine moving blade throat•pitch ratio to swell by giving the blade untwisting angle to the blade cross-sections in regions where the aerodynamic loss is small. The steam turbine is one in which the throat•pitch ratio (S/T) distribution of a turbine moving blade is offset by forming a curve providing at least one minimal value and maximal value by giving blade twist angle to the blade cross-sections in the blade height direction from blade root to blade tip and, at the same time, the distribution of throat•pitch ratio (S/T) taking into consideration blade untwist generated during operation.

High efficiency blade configuration for steam turbine

A steam turbine that passes more turbine driving steam by off-setting the turbine moving blade throat· pitch ratio before operation and, when a blade untwist is generated during operation, causing more turbine driving steam to flow by maintaining an appropriate value, and, at the same time causing the turbine moving blade throat· pitch ratio to swell by giving the blade untwisting angle to the blade cross-sections in regions where the aerodynamic loss is small. The steam turbine according to this present invention is one in which the throat· pitch ratio (S/T) distribution of a turbine moving blade is offset by forming a curve providing at least one minimal value and maximal value by giving blade twist angle to the blade cross-sections in the blade height direction from blade root to blade tip and, at the same time, the distribution of throat· pitch ratio (S/T) taking into consideration blade untwist generated during operation.

Blade configuration for steam turbine

PURPOSE: A vapor turbine is provided to make more turbine driving vapor flow by making the turbine driving vapor stably flow and expanding the throat*S/T of the turbine wing CONSTITUTION: The vapor turbine is composed of; a turbine stage(22) consisting with the combination of a turbine nozzle blade(20) supported by an inner diaphragm(23) and an outer diaphragm(24) and a turbine movable blade(21) filled in a turbine shaft(25); plural turbine stages(22) arranged along the turbine shaft(25); the turbine movable blade(21) having a blade filling unit(26) and a blade available unit(27); and an intermediate connecting unit(29) installed on a position of 50 to 70% of blade height to reduce the vibration of the turbine movable blade(21) and to prevent the untwist of the turbine movable blade(21)

Taro Sakamoto

Papers

High efficiency blade configuration for steam turbine

Blade configuration for steam turbine

Wing form of high performance for vapor turbine