COOLED TURBINE BLADE WITH DOUBLE COMPOUND ANGLED HOLES AND SLOTS

• US 20140369852A1
• Filed: 06/14/2013
• Published: 12/18/2014
• Est. Priority Date: 06/14/2013
• Status: Active Grant

• Current Assignee: Solar Turbines Incorporated (Caterpillar Incorporated)
• Original Assignee: Solar Turbines Incorporated (Caterpillar Incorporated)
• Inventors: Zhang, Luzeng, Yin, Juan, Moon, Hee Koo
• Granted Patent: US 9,464,528 B2
• Time in Patent Office: Days
• US Class Current: 416/97.A
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2250/324 divergent
• CPC Class Codes: F05D 2260/202 by film cooling

Abstract

A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and having an outer wall, an airfoil air passageway, a plurality of trailing edge slots in fluid communication with the airfoil air passageway and a plurality of directional film holes through the outer wall in fluid communication with the airfoil air passageway. The plurality of directional film holes includes a first portion configured to discharge the cooling air toward a tip end, and a second portion configured to discharge the cooling air toward the platform.

Claims

1. A turbine blade for use in a gas turbine engine, the turbine blade, the turbine blade having a tip end and a root end, the turbine blade comprising:

a base including a blade root, a platform, a cooling air inlet, and a base air passageway within the base, the base air passageway configured to receive and route cooling air from the cooling air inlet; and

an airfoil section adjoined to the base, the airfoil section including

an outer wall extending from the base to a tip end, the outer wall forming a leading edge, a trailing edge, a pressure side, and a suction side,

an airfoil air passageway within the outer wall, the airfoil air passageway configured to receive and route the cooling air from the base air passageway,

a plurality of trailing edge slots in fluid communication with the airfoil air passageway and configured to discharge a first percentage of the cooling air from the airfoil section, and

a plurality of directional film holes through the outer wall and each having a film hole inlet and a film hole outlet, the film hole inlet located forward of the film hole outlet, the plurality of directional film holes in fluid communication with the airfoil air passageway and configured to discharge a second percentage of the cooling air,

a first portion of the plurality of directional film holes each having the film hole inlet located closer to the platform than the film hole outlet, respectively, and

a second portion of the plurality of directional film holes located closer to the platform than the first portion of the plurality of directional film holes, each of the second portion of the plurality of directional film holes having the film hole outlet located closer to the platform than the film hole inlet, respectively.

2. The turbine blade of claim 1, wherein the first portion of the plurality of directional film holes are stratified between the tip end and a film transition line;

wherein the second portion of the plurality of directional film holes are stratified between the film transition line and the platform; and

wherein the plurality of directional film holes distributed spanwise with a pitch-to-diameter ratio (P/D) range of 2-7.

3. The turbine blade of claim 1, wherein the first portion of the plurality of directional film holes extend from a film transition line as a first single-column spanwise array toward the tip end;

wherein the second portion of the plurality of directional film holes extend from the film transition line as a second single-column spanwise array toward the platform;

wherein one of the first single-column spanwise array and the second single-column spanwise array is positioned upstream of the other;

wherein one of the first portion of the plurality of directional film holes is positioned on or between the film transition line and the platform; and

wherein one of the second portion of the plurality of directional film holes is positioned on or between the film transition line and the tip end.

4. The turbine blade of claim 1, wherein an upper portion of the plurality of trailing edge slots are further configured to discharge cooling air from the turbine blade upward at a first trailing edge angle, relative to the platform as a ground;

and

wherein a lower portion of the plurality of trailing edge slots are further configured to discharge cooling air from the turbine blade downward at a second trailing edge angle, relative to the platform;

wherein the plurality of trailing edge slots include a fan slot positioned between the upper portion of the plurality of trailing edge slots and the lower portion of the plurality of trailing edge slots, the fan slot configured to discharge cooling air upward, downward, and in between;

wherein the first portion of the plurality of directional film holes and the upper portion of the plurality of trailing edge slots extend between a film transition line and the tip end; and

wherein the second portion of the plurality of directional film holes and the lower portion of the plurality of trailing edge slots extend between the film transition line and the platform.

5. A turbine rotor assembly for use in a gas turbine engine including a plurality of turbine blades as described in claim 1, turbine rotor assembly comprising rotor disk that is circumferentially populated with the plurality of the turbine blades.

6. A turbine blade for use in a gas turbine engine, the turbine blade, the turbine blade having a tip end and a root end, the turbine blade comprising:

a base including a blade root, a platform, a cooling air inlet, and a base air passageway within the base, the base air passageway configured to receive and route cooling air from the cooling air inlet; and

an airfoil section adjoined to the base, the airfoil section including

an outer wall extending from the base to a tip end, the outer wall forming a leading edge, a trailing edge, a pressure side, and a suction side,

an airfoil air passageway within the outer wall, the airfoil air passageway configured to receive and route the cooling air from the base air passageway,

a plurality of trailing edge slots in fluid communication with the airfoil air passageway and configured to discharge a first percentage of the cooling air from the airfoil section, and

a plurality of directional film holes through the pressure side of the outer wall, the plurality of directional film holes in fluid communication with the airfoil air passageway and configured to discharge a second percentage of the cooling air,

a first portion of the plurality of directional film holes configured to discharge the cooling air toward the tip end, and

a second portion of the plurality of directional film holes configured to discharge the cooling air toward the root end.

7. The turbine blade of claim 6, wherein the plurality of directional film holes are positioned downstream from the leading edge between sixty and ninety percent of a length from the leading edge to the trailing edge;

and

wherein the plurality of directional film holes each include a film hole discharge angle from the outer wall between 15 degrees and 45 degrees.

8. The turbine blade of claim 6, wherein the first portion of the plurality of directional film holes extend from a film transition line as a first single-column spanwise array toward the tip end;

wherein the second portion of the plurality of directional film holes extend from the film transition line as a second single-column spanwise array toward the platform;

wherein one of the first single-column spanwise array and the second single-column spanwise array is positioned upstream of the other;

wherein one of the first portion of the plurality of directional film holes is positioned on or between the film transition line and the platform; and

wherein one of the second portion of the plurality of directional film holes is positioned on or between the film transition line and the tip end.

9. The turbine blade of claim 6, wherein an upper portion of the plurality of trailing edge slots are further configured to discharge cooling air from the turbine blade upward at a first trailing edge angle, relative to the platform as a ground;

and

wherein a lower portion of the plurality of trailing edge slots are further configured to discharge cooling air from the turbine blade downward at a second trailing edge angle, relative to the platform.

10. The turbine blade of claim 9, wherein the plurality of trailing edge slots include a fan slot positioned between the upper portion of the plurality of trailing edge slots and the lower portion of the plurality of trailing edge slots, the fan slot configured to discharge cooling air upward, downward, and in between;

wherein the first portion of the plurality of directional film holes and the upper portion of the plurality of trailing edge slots extend between a film transition line and the tip end; and

wherein the second portion of the plurality of directional film holes and the lower portion of the plurality of trailing edge slots extend between the film transition line and the platform.

11. A turbine blade for use in a gas turbine engine, the turbine blade comprising:

a base including a blade root, a platform, a cooling air inlet, and a base air passageway within the base, the base air passageway configured to receive and route cooling air from the cooling air inlet; and

an airfoil section adjoined to the base, the airfoil section including

an outer wall extending from the base to a tip end, the outer wall forming a leading edge, a trailing edge, a pressure side, and a suction side,

an airfoil air passageway within the outer wall, the airfoil air passageway configured to receive and route the cooling air from the base air passageway,

a plurality of trailing edge slots in fluid communication with the airfoil air passageway and configured to discharge a first percentage of the cooling air from the airfoil section, and

a plurality of directional film holes through the outer wall and positioned downstream from the leading edge by at least half of a length from the leading edge to the trailing edge, the plurality of directional film holes in fluid communication with the airfoil air passageway and configured to discharge a second percentage of the cooling air,

a first portion of the plurality of directional film holes configured to discharge the cooling air toward the tip end, and

a second portion of the plurality of directional film holes configured to discharge the cooling air toward the platform.

12. The turbine blade of claim 11, wherein the plurality of directional film holes are positioned downstream from the leading edge between sixty and ninety percent of the length from the leading edge to the trailing edge.

13. The turbine blade of claim 11, wherein the first portion of the plurality of directional film holes extend as a first single-column spanwise array having a first beginning directional film hole nearest the tip end and a first ending directional film hole farthest from the tip end;

wherein the second portion of the plurality of directional film holes extend from as a second single-column spanwise array having a second beginning directional film hole nearest the platform and a second ending directional film hole farthest from the platform; and

wherein the first ending directional film hole is equidistant or closer to the platform than the second ending directional film hole.

14. The turbine blade of claim 13, wherein one of the first single-column spanwise array and the second single-column spanwise array is positioned upstream of the other;

wherein one of the first portion of the plurality of directional film holes is positioned on or between a film transition line and the platform; and

wherein one of the second portion of the plurality of directional film holes is positioned on or between the film transition line and the tip end.

15. The turbine blade of claim 11, wherein the plurality of directional film holes each include a film hole discharge angle from the outer wall between 15 degrees and 45 degrees.

16. The turbine blade of claim 11, wherein the first portion of the plurality of directional film holes is further configured to discharge cooling air upward at a first target angle between 10 degrees and 40 degrees in a positive direction;

and

wherein the second portion of the plurality of directional film holes is further configured to discharge cooling air downward at a second target angle between 10 degrees and 40 degrees in a negative direction.

17. The turbine blade of claim 11, wherein an upper portion of the plurality of trailing edge slots are further configured to discharge cooling air from the turbine blade upward at a first trailing edge angle;

and

wherein a lower portion of the plurality of trailing edge slots are further configured to discharge cooling air from the turbine blade downward at a second trailing edge angle, relative to the platform as a ground.

18. The turbine blade of claim 17, wherein the first trailing edge angle is between 10 degrees and 40 degrees in a positive direction and the second trailing edge angle is between 10 degrees and 40 degrees in the negative direction.

19. The turbine blade of claim 17, wherein the first portion of the plurality of directional film holes is further configured to discharge cooling air upward at a first target angle, the first target angle substantially the same as the first trailing edge angle;

and

wherein the second portion of the plurality of directional film holes is further configured to discharge cooling air downward at a second target angle, the second target angle substantially the same as the second trailing edge angle;

wherein the plurality of trailing edge slots include a fan slot positioned between the upper portion of the plurality of trailing edge slots and the lower portion of the plurality of trailing edge slots, the fan slot configured to discharge cooling air upward, downward, and in between;

wherein the first portion of the plurality of directional film holes and the upper portion of the plurality of trailing edge slots extend between a film transition line and the tip end; and

wherein the second portion of the plurality of directional film holes and the lower portion of the plurality of trailing edge slots extend between the film transition line and the platform.

20. A gas turbine engine including a turbine having a turbine rotor assembly that includes the turbine blade of claim 11, the gas turbine engine comprising;

and

wherein the turbine rotor assembly is installed in a first stage of the turbine.