Turbine rotor blade

Patent metadata

Field	Value
Publication number	US-9765628-B2
Application number	US-201113702557-A
Country	US
Kind code	B2
Filing date	Dec 7, 2011
Priority date	Dec 7, 2011
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A turbine rotor blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the blade and suppress degradation in performance even if cooling air mixes in toward the blade. The rotor blade is mounted to a rotor to form a turbine blade row rotating in a stationary member that includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is smaller on the downstream side than on the upstream side.

First claim

The invention claimed is:

1. A turbine rotor blade mounted to a rotor to form a rotating turbine blade row, comprising:
a platform forming a gas passage through which a mainstream gas flows; and
an airfoil extending from a gas passage plane in a radial direction in which a distance from a rotational axis of the rotor increases, the gas passage plane being a plane of the platform and forming the gas passage; wherein
the airfoil has, in an end face of a tip-side thereof, an area where an inclination with respect to the rotational axis is varied,
a blade height which is a length of the airfoil in the radial direction is configured such that a blade height at a leading edge of the airfoil is lower than a blade height at a throat position on a suction surface of the airfoil,
the tip-side end face of the airfoil has a plurality of steps as the area where the inclination is varied, at a position between the leading edge and the throat position on the suction surface of the airfoil,
cross-sections formed by the steps are continuous with the suction surface from the throat position on the suction surface or from an upstream side of the throat position, and
a leading edge portion of the steps is formed to have a curvature smaller than that of a leading edge portion of a face at which a radial distance from the rotational axis is the shortest at the tip-side end face of the airfoil.

2. The turbine rotor blade according to claim 1 , wherein the airfoil is internally provided with a cooling passage adapted to allow a cooling medium to flow.

3. The turbine rotor blade according to claim 2 , wherein the tip-side end face of the airfoil is provided with a discharge hole adapted to discharge the cooling medium flowing down the cooling passage and the discharge hole is located on the upstream side of the step in the flow direction of the mainstream gas.

4. A gas turbine comprising:
a casing, which is a stationary member;
a rotor rotating in the casing; and
a turbine rotor blade mounted to the rotor to form a turbine blade row rotating in the stationary member; wherein
the turbine rotor blade includes a platform forming a gas passage through which a mainstream gas flows, and an airfoil extending from a gas passage plane in a radial direction vertical to a rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage,
the airfoil has a plurality of steps in an end face of a tip-side thereof,
cross-sections formed by the steps are continuous with a suction surface of the airfoil from a throat position on the suction surface or from an upstream side of the throat position,
a leading edge portion of the steps is formed to have a curvature smaller than that of a leading edge portion of a face at which a radial distance from the rotational axis is the shortest at the tip-side end face of the airfoil, and
a clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is defined so that a clearance at a leading edge of the airfoil may be greater than that at a throat position on the suction surface of the airfoil.

5. A method for cooling a turbine rotor blade mounted to a rotor to form a turbine blade row rotating in a stationary member, the turbine rotor blade including a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to a rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage, wherein the airfoil has a plurality of steps in an end face of a tip-side thereof, a blade height, which is a length of the airfoil in the radial direction, is higher on a downstream side in a flow direction of the mainstream gas than on an upstream side, a clearance between a tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is defined to reduce stepwise in the flow direction of the mainstream gas, cross-sections formed by the steps are continuous with a suction surface of the airfoil from a throat position on the suction surface or from an upstream side of the throat position, a leading edge portion of the steps is formed to have a curvature smaller than that of a leading edge portion of a face at which a radial distance from the rotational axis is the shortest at the tip-side end face of the airfoil, the method comprising:
supplying a cooling medium to the plurality of steps to cool the tip-side of the airfoil.

Assignees

• Miyoshi Ichiro
• Higuchi Shinichi
• Noda Masami
• Mitsubishi Hitachi Power Sys

Inventors

• Miyoshi Ichiro
• Higuchi Shinichi
• Noda Masami

Classifications

• F01D5/187

  Convection cooling · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title