Rotor blade having a flared tip

Patent metadata

Field	Value
Publication number	US-10107108-B2
Application number	US-201514699321-A
Country	US
Kind code	B2
Filing date	Apr 29, 2015
Priority date	Apr 29, 2015
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.

First claim

What is claimed is:

1. A rotor blade, comprising:
an airfoil having a leading edge and a trailing edge, a pressure side wall and a suction side wall connected at the leading and trailing edges, a blade tip having a continuous radially outer surface, and an internal cavity for receiving a cooling medium, wherein the continuous radially outer surface of the blade tip extends along the pressure side wall from the leading edge to the trailing edge, across the trailing edge from the pressure side wall to the suction side wall, along the suction side wall from the trailing edge to the leading edge, and across the leading edge from the suction side wall to the pressure side wall, the airfoil further comprising:
a tip cavity formed at the blade tip, the tip cavity including a tip cap recessed radially inwardly from the continuous radially outer surface of the blade tip, the tip cap continuously surrounded by and connected to the pressure and suction side walls along a periphery of the tip cap between the leading edge and the trailing edge, wherein the tip cap further includes an aperture that extends through an inner surface and a radially opposed top surface of the tip cap and provides for fluid communication between the internal cavity and the tip cavity, and an exhaust port that extends through the trailing edge between the top surface of the tip cap and the continuous radially outer surface of the blade tip and provides for fluid communication from the tip cavity through the trailing edge, the exhaust port tapered such that an inlet of the exhaust port has a smaller cross sectional area than an outlet of the exhaust port;
wherein an inner surface of the suction side wall that defines the tip cavity extends obliquely outwardly with respect to a radial direction from the tip cavity to the continuous radially outer surface of the blade tip, wherein the exhaust port extends through the continuous radially outer surface of the blade tip at the trailing edge of the airfoil, and wherein the exhaust port is in fluid communication with the tip cavity.

2. The rotor blade as in claim 1 , further comprising a trench defined within the top surface of the tip cap.

3. The rotor blade as in claim 2 , wherein the trench extends along a camber line of the airfoil.

4. The rotor blade as in claim 2 , wherein the trench extends along a camber line of the airfoil from the trailing edge towards the leading edge of the airfoil.

5. The rotor blade as in claim 1 , wherein the aperture that extends through the inner and top surfaces of the tip cap is angled towards the trailing edge of the airfoil.

6. The rotor blade as in claim 1 , further comprising a hole defined along the trailing edge of the airfoil and positioned radially below the tip cap, wherein the hole is in fluid communication with the internal cavity.

7. A gas turbine, comprising:
a compressor section;
a combustion section; and
a turbine section, the turbine section having a rotor shaft and a plurality of rotor blades coupled to the rotor shaft, each rotor blade comprising:
an airfoil having a leading edge and a trailing edge, a pressure side wall and a suction side wall connected at the leading and trailing edges, a blade tip having a continuous radially outer surface, and an internal cavity for receiving a cooling medium, wherein the continuous radially outer surface of the blade tip extends along the pressure side wall from the leading edge to the trailing edge, across the trailing edge from the pressure side wall to the suction side wall, along the suction side wall from the trailing edge to the leading edge, and across the leading edge from the suction side wall to the pressure side wall, the airfoil further comprising:
a tip cavity formed at the blade tip, the tip cavity including a tip cap recessed radially inwardly from the continuous radially outer surface of the blade tip, the tip cap continuously surrounded by and connected to the pressure and suction side walls along a periphery of the tip cap between the leading edge and the trailing edge, wherein the tip cap further includes an aperture that extends through an inner surface and a radially opposed top surface of the tip cap and provides for fluid communication between the internal cavity and the tip cavity, and an exhaust port in fluid communication with the tip cavity, the exhaust port extends through the trailing edge from an inlet between the top surface of the tip cap and the continuous radially outer surface of the blade tip to an outlet in the continuous radially outer surface of the blade tip at the trailing edge of the airfoil and provides for fluid communication from the tip cavity through the trailing edge;
wherein an inner surface of the suction side wall that defines the tip cavity extends obliquely outwardly with respect to a radial direction from the tip cavity to the continuous radially outer surface of the blade tip.

8. The gas turbine as in claim 7 , further comprising a trench defined within the top surface of the tip cap, wherein the trench extends along a camber line of the airfoil from the trailing edge towards the leading edge of the airfoil.

9. The gas turbine as in claim 7 , further comprising a hole defined along the trailing edge of the airfoil and positioned radially below the tip cap, wherein the hole is in fluid communication with the internal cavity.

Assignees

• Gen Electric

Inventors

• Jones Jeffrey Clarence
• Zhang Xiuzhang James
• Merrill Mitchell Allan

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/20 Primary

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

• F05D2250/324

  divergent · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title