Turbine blade, turbine including same turbine blade, and gas turbine including same turbine

Patent metadata

Field	Value
Publication number	US-10871073-B2
Application number	US-201816034321-A
Country	US
Kind code	B2
Filing date	Jul 12, 2018
Priority date	Sep 18, 2017
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

Abstract

A turbine blade is provided with a rotatable leading edge to reduce pressure loss as a flow direction of combustion gas varies. The turbine blade includes an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the leading-edge portion including a front surface arranged on an upstream side of the leading-edge portion; and a rotary unit connected to the leading-edge portion and configured to rotate the leading-edge portion according to an inflow angle of the combustion gas such that the front surface faces a flow of the combustion gas. A barrier wall extends from a side surface of the leading-edge portion toward an open end of the trailing edge portion, and when the leading-edge portion is rotated, the barrier wall portion prevents formation of a gap between the side surface and the open end.

First claim

What is claimed is:

1. A turbine blade mounted on a turbine disk in a turbine casing of a turbine, the turbine blade rotating the turbine when combustion gas flows in the turbine casing, the turbine blade comprising:
an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the trailing-edge portion including first and second sides opposing each other and forming an open end linked to the leading-edge portion and a closed end having a streamlined shape, the leading-edge portion including a front surface arranged on an upstream side of the leading-edge portion;
a rotary unit connected to the leading-edge portion and configured to rotate the leading-edge portion according to an inflow angle of the combustion gas such that the front surface faces a flow of the combustion gas; and
a generally U-shaped barrier wall portion configured to prevent formation of a gap between the open end of the trailing-edge portion and either of a first side surface of the leading-edge portion and a second side surface of the leading-edge portion, the generally U-shaped barrier wall portion comprising:
a first wall having an upstream portion exposed to the combustion gas and protruding axially from the first side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a first distal end and inner and outer surfaces joined at the first distal end, the outer surface of the first wall configured to contact an inside surface of the first side of the trailing-edge portion; and
a second wall having an upstream portion exposed to the combustion gas and protruding axially from the second side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a second distal end and inner and outer surfaces joined at the second distal end, the outer surface of the second wall configured to contact an inside surface of the second side of the trailing-edge portion.

2. The turbine blade according to claim 1 , wherein the distal end of each of the first wall and the second wall has a shape corresponding to a periphery of the open end of the trailing-edge.

3. The turbine blade according to claim 1 , wherein the leading-edge portion further includes a rear surface arranged toward the open end of the trailing-edge portion, and the front and rear surfaces of the leading-edge portion have semicircular cross-sections with different radii.

4. The turbine blade according to claim 3 , wherein the rear surface has a larger radius than the front surface.

5. The turbine blade according to claim 3 , wherein each the side surface of the leading-edge portion includes a boundary between the front and rear surfaces, and the barrier wall portion is connected to the leading-edge portion at the boundary.

6. The turbine blade according to claim 1 , further comprising: a root member for coupling, the airfoil to the turbine disk; and a platform formed on an upper portion of the root member and configured to receive the airfoil in an oblong cavity formed on an upper surface of the platform.

7. The turbine blade according, to claim 6 , wherein the trailing-edge portion of the airfoil of the turbine blade is fixed in the oblong cavity separately from the leading-edge portion.

8. The turbine blade according to claim 1 , wherein the rotary unit comprises:
a mounting end coupled to the leading-edge portion of the airfoil of the turbine blade; a servo motor configured to rotate the leading-edge portion of the airfoil of the turbine blade in forward and reverse directions; and a controller configured to control operation of the servo motor according to the inflow angle of the combustion gas.

9. The turbine blade according to claim 8 , further comprising: a sensor to measure the inflow angle of the combustion gas at the front surface of the leading-edge portion and to output information indicative of the measured inflow angle to the controller.

10. The turbine blade according to claim 8 , wherein the servo motor, under control of the controller, rotates the leading-edge portion according to a flow direction of combustion gas striking the front surface of the leading-edge portion.

11. A turbine for generating driving force to be used for generation of electric power by passing a combustion gas supplied from a combustor, the turbine comprising:
a turbine casing in which the combustion gas flows; and
a turbine rotor rotatable inside the turbine casing, the turbine rotor including a plurality of turbine disks and a plurality of turbine blades coupled to an outer surface of each of the plurality of turbine disks, wherein a turbine blade of the plurality of turbine blades comprises:
an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the trailing-edge portion including first and second sides opposing each other and forming an open end linked to the leading-edge portion and a closed end having a streamlined shape, the leading-edge portion including a front surface arranged on an upstream side of the leading-edge portion;
a rotary unit connected to the leading-edge portion and configured to rotate the leading-edge portion according to an inflow angle of the combustion gas such that the front surface faces a flow of the combustion gas; and
a generally U-shaped barrier wall portion configured to prevent formation of a gap between the open end of the trailing-edge portion and either of a first side surface of the leading-edge portion and a second side surface of the leading-edge portion, the generally U-shaped barrier wall portion comprising:
a first wall having an upstream portion exposed to the combustion gas and protruding axially from the first side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a first distal end and inner and outer surfaces joined at the first distal end, the outer surface of the first wall configured to contact an inside surface of the first side of the trailing-edge portion; and
a second wall having an upstream portion exposed to the combustion gas and protruding axially from the second side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a second distal end and inner and outer surfaces joined at the second distal end, the outer surface of the second wall configured to contact an inside surface of the second side of the trailing-edge portion.

12. A gas turbine comprising:
a compressor to produce compressed air by taking in air and compressing the intake air;
a combustor to produce combustion gas by burning a mixture of fuel and the compressed air supplied from the compressor; and
a turbine rotatable by the combustion gas supplied from the combustor, the turbine comprising:
a turbine casing in which the combustion gas flows; and
a turbine rotor rotatable inside the turbine casing, the turbine rotor including a plurality of turbine disks and a plurality of turbine blades coupled to an outer surface of each of the plurality of turbine disks,
wherein a turbine blade of the plurality of turbine blades comprises an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the trailing-edge portion including first and second sides opposing each other and forming an open end linked to the leading-edge portion and a closed end having a streamlined shape, the leading-edge portion incl

Assignees

• Doosan Heavy Ind & Construction Co Ltd
• Doosan Heavy Ind Constr Co Ltd

Inventors

• Lee Ik Sang

Classifications

• 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

• F05D2260/57

  using servos, independent actuators, etc. · CPC title

• F05D2260/76

  the adjusting mechanism using auxiliary power sources · CPC title

• F01D5/148 Primary

  Blades with variable camber, e.g. by ejection of fluid · CPC title

• F02C9/22

  by adjusting turbine vanes · CPC title