Gas turbine engines with improved airfoil dust removal

Patent metadata

Field	Value
Publication number	US-11199099-B2
Application number	US-202016826953-A
Country	US
Kind code	B2
Filing date	Mar 23, 2020
Priority date	Nov 13, 2017
Publication date	Dec 14, 2021
Grant date	Dec 14, 2021

Abstract

An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

First claim

What is claimed is:

1. An airfoil for a rotor blade in a gas turbine engine, comprising:
a first side wall;
a second side wall joined to the first side wall at a leading edge and a trailing edge, the first and second side walls extending in a radial outward direction from a base coupled to an airfoil platform;
a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip; and
an internal cooling system arranged within the first and second side walls configured to direct cooling air from one or more source passages, through the airfoil, and out of the airfoil, the internal cooling system includes a leading edge cooling circuit, and a trailing edge cooling circuit, the internal cooling system further including tip slots formed in the blade tip and trailing edge slots formed in the trailing edge and the tip slots are formed in the blade tip to extend from the leading edge to the trailing edge,
wherein the leading edge cooling circuit, and the trailing edge cooling circuit are formed by a plurality of internal passages fluidly coupled to the one or more source passages, and each of the internal passages within the leading edge cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis, and the leading edge cooling circuit includes:
a first leading radial passage extending in the radial outward direction and at least partially defined by a first leading radial wall in a chordwise aft direction, the tip cap in the radial outward direction, and a second leading radial wall in a chordwise forward direction; and
a second leading radial passage at least partially defined by the leading edge in the chordwise forward direction, the tip cap in the radial outward direction, and the second leading radial wall in the chordwise aft direction, and the second leading radial wall includes a plurality of cooling holes that fluidly couple the first leading radial passage to the second leading radial passage and the tip slots in the blade tip defined along the second leading radial passage form the at least one escape hole for the second leading radial passage;

the trailing edge cooling circuit includes:
a first set of serpentine passages formed by a first trailing radial passage extending in the radial outward direction from the one or more source passages, a second trailing radial passage extending in a radial inward direction from the first trailing radial passage at a first transition, and a third trailing radial passage extending from the second trailing radial passage in the radial outward direction, the first trailing radial passage defined in the chordwise forward direction by the first leading radial wall and at least partially by an internal wall in the chordwise aft direction and the third trailing radial passage extending in the radial outward direction and being formed by a first radial wall in the chordwise forward direction and a second radial wall in the chordwise aft direction; and
a trailing edge chamber being at least partially formed by the second radial wall in the chordwise forward direction and the trailing edge in the chordwise aft direction, the second radial wall defining holes that fluidly couple the third trailing radial passage to the trailing edge chamber,

wherein the trailing edge chamber is fluidly coupled to the trailing edge slots and is bounded in the radial outward direction by the tip cap such that at least a portion of the tip slots form the at least one escape hole for the trailing edge chamber.

2. The airfoil of claim 1 , wherein at least one wall bounding each of the internal passages within the leading edge cooling circuit, and the trailing edge cooling circuit in the radial outward direction includes the at least one escape hole.

3. The airfoil of claim 1 , wherein the second trailing radial passage is fluidly coupled to the first trailing radial passage at the first transition formed by the tip cap such that a second portion of the cooling air in the first trailing radial passage flows through the transition into the second trailing radial passage and in a radial inward direction through the second trailing radial passage.

4. The airfoil of claim 1 , wherein the first trailing radial passage is bounded in the radial outward direction by the tip cap such that at least a portion of the tip slots form the at least one escape hole for the first trailing radial passage.

5. The airfoil of claim 1 , wherein each of the tip slots have a converging cross-sectional area from an inlet to an outlet.

6. The airfoil of claim 1 , wherein each of the trailing edge slots have a converging cross-sectional area from an inlet to an outlet.

7. The airfoil of claim 1 , wherein the second trailing radial passage is defined in the chordwise forward direction at least partially by the internal wall and at least partially by the first radial wall in the chordwise aft direction.

8. An airfoil for a rotor blade in a gas turbine engine, comprising:
a first side wall;
a second side wall joined to the first side wall at a leading edge and a trailing edge, the first and second side walls extending in a radial outward direction from a base coupled to an airfoil platform;
a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip; and
an internal cooling system arranged within the first and second side walls configured to direct cooling air from one or more source passages, through the airfoil, and out of the airfoil, the one or more source passages including at least a first source passage, a second source passage, a third source passage and a fourth source passage, the cooling air received at a first source inlet of the first source passage, a second source inlet of the second source passage, a third source inlet of the third source passage and a fourth source inlet of the fourth source passage,
wherein the internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit, the internal cooling system further including tip slots formed in the blade tip and trailing edge slots formed in the trailing edge, and
wherein the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit are formed by a plurality of internal passages fluidly coupled to the one or more source passages, and wherein each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis and the leading edge cooling circuit includes:
a first leading radial passage extending in the radial outward direction and at least partially defined by a first radial wall in a chordwise aft direction, the tip cap in the radial outward direction, and a second radial wall in a chordwise forward direction, the first leading radial passage fluidly coupled to the first source passage;
a second leading radial passage at least partially defined by the leading edge in the chordwise forward direction, the tip cap in the radial outward direction, and the second radial wall in the chordwise aft direction, and
wherein the second radial wall includes a plurality of cooling holes that fluidly couple the first leading radial passage to the second leading radial passage and the tip slots in the blade tip form the at le

Assignees

• Honeywell Int Inc

Inventors

• Crites Daniel C
• Kahrs Michael
• Wakefield Brandan
• Riahi Ardeshir

Classifications

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/2212

  by creating turbulence · CPC title