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US 10,895,168 B2Granted
Turbine blade with serpentine channels
AssigneeSolar Turbines Incorporated
InventorHongzhou Xu
Life of this patent
Estimating the term…
Abstract
A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a leading edge, a trailing edge, having a tip end opposite from the root end. The turbine blade further including dividers located within the airfoil. The dividers, leading edge, trailing edge, and skin define serpentine channels within the airfoil. A first multi-bend heat exchange path and a second multi-bend heat exchange path extend through the serpentine channels to cool portion of the turbine blade.
Claims20
A turbine blade for use in a gas turbine engine, the turbine blade comprising:
- a base including
- a root end,
- a forward face,
- an aft face located opposite the forward face,
- a first inlet located proximate to the forward face, and
- a second inlet located between the first inlet and the aft face;
- an airfoil comprising
- a skin extending from the base and defining a leading edge, a trailing edge opposite the leading edge, a pressure side, and a suction side opposite the pressure side, and having a tip end opposite from the root end;
- a first transition portion extending from adjacent the first inlet towards the leading edge;
- a first rib portion extending from the first transition portion opposite the root end towards the tip end, and having a first end located opposite from the root end,
- a third transition portion extending from the leading edge towards the trailing edge, located proximate to the tip end, and located between the first end and the tip end;
- a third rib portion extending from the third transition portion towards the root end, located between the first rib portion and the trailing edge, the third rib portion located proximate to the first rib portion, and having a third end located opposite from the tip end;
- a second transition portion extending from adjacent the second inlet towards the trailing edge;
- a second rib portion extending from the second transition portion opposite the root end towards the tip end, the second rib portion located between the third rib portion and the trailing edge, the second rib portion having a second end located opposite the root end;
- a fourth transition portion extending from the trailing edge towards the leading edge, located between the second end and the tip end;
- a fourth rib transition portion extending from the fourth transition portion towards the root end, the fourth rib transition portion located between the third rib portion and the trailing edge;
- and
- a fourth rib portion extending from proximate the fourth transition portion, towards the root end, the fourth rib portion located between the third rib portion and the second rib portion, and the fourth rib portion having a fourth end located opposite from the tip end.
15 more elements
A turbine blade for use in a gas turbine engine, the turbine blade comprising:
- a base including
- a root end;
- an airfoil comprising
- a skin extending from the base and defining a leading edge, a trailing edge opposite the leading edge, a pressure side, and a suction side opposite the pressure side, and having a tip end opposite from the root end;
- a first divider located within the airfoil and the base, extending from within the base and into the airfoil, and having a first end located opposite from the base;
- a third divider located within the airfoil, a portion of the third divider extending from the leading edge towards the trailing edge, located proximate to the tip end, and the third divider partially located between the first divider and the trailing edge;
- a second divider located within the airfoil and the base, extending from the base and into the airfoil, partially located between the third divider and the trailing edge, the second divider having a second end located opposite from the base;
- and
- a fourth divider located within the airfoil, a portion of the fourth divider extending from the trailing edge towards the leading edge and located between the second divider and the tip end, the fourth divider partially located between the third divider and the second divider, and the fourth divider having a fourth end located opposite from the tip end.
6 more elements
A turbine blade for use in a gas turbine engine, the turbine blade comprising:
- a base including
- a root end,
- a forward face,
- an aft face located opposite the forward face,
- a first inlet located proximate to the forward face, and
- a second inlet located between the first inlet and the aft face;
- an airfoil comprising
- a skin extending from the base and defining a leading edge, a trailing edge opposite the leading edge, a pressure side, and a suction side opposite the pressure side, and having a tip end opposite from the root end;
- a first transition portion extending from adjacent the first inlet towards the leading edge;
- a first rib portion extending from the first transition portion towards the tip end, and having a first end located opposite from the root end;
- a third transition portion extending from the leading edge towards the trailing edge, located proximate to the tip end;
- a third rib portion extending from the third transition portion towards the root end, located between the first rib portion and the trailing edge, the third rib portion having a third end;
- a fifth rib portion extending from proximate the third end towards the tip end, the fifth rib portion located between the third rib portion and the trailing edge;
- and
- a fifth transition portion extending from the fifth rib portion radially towards the tip end and extending from the fifth rib portion circumferentially towards the trailing edge.
12 more elements
Dependencies are inferred from the claim text.