Cooled turbine blade with double compound angled holes and slots

• US 9,464,528 B2
• Filed: 06/14/2013
• Issued: 10/11/2016
• 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
• Primary Examiner(s): Keasel, Eric
• Assistant Examiner(s): CORDAY, CAMERON A
• Application Number:
  US13/918,052
• Publication Number:
  US 20140369852A1
• Time in Patent Office: 1,215 Days
• US Class Current: 1/1
• 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 a gas turbine engine, 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 being configured to receive cooling air from the cooling air inlet and route the cooling air through the base air passageway; and

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

an outer wall extending from the base to the 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 the cooling air from the base air passageway and route the cooling air through the airfoil 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, each film hole of the plurality of directional film holes having a film hole inlet and a film hole outlet, the film hole inlet being located closer to the leading edge than the film hole outlet, the plurality of directional film holes being in fluid communication with the airfoil air passageway and being configured to discharge a second percentage of the cooling air,

the plurality of directional film holes including a first portion of film holes and a second portion of film holes,

each film hole of the first portion of film holes having the film hole inlet located closer to the platform than the film hole outlet, respectively, and being configured to discharge the cooling air toward the tip end at a first target angle relative to the platform,

the second portion of film holes being located closer to the platform than the first portion of film holes,

each film hole of the second portion of film holes having the film hole outlet located closer to the platform than the film hole inlet, respectively, and being configured to discharge the cooling air toward the platform at a second target angle relative to the platform, wherein

an upper portion of the plurality of trailing edge slots is configured to discharge the cooling air from the turbine blade upward at a first trailing edge angle relative to the platform,

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

the first target angle is substantially the same as the first trailing edge angle,

the second target angle is substantially the same as the second trailing edge angle,

the plurality of trailing edge slots includes 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 being configured to discharge the cooling air upward, downward, and in between,

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

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

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

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

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

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

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

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

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

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

4. A turbine rotor assembly for the gas turbine engine including a plurality of turbine blades, each turbine blade of the plurality of turbine blades being the turbine blade of claim 1, the turbine rotor assembly comprising a rotor disk that is circumferentially populated with the plurality of turbine blades.

5. A turbine blade for a gas turbine engine, 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 being configured to receive cooling air from the cooling air inlet and route the cooling air through the base air passageway; 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 being configured to receive the cooling air from the base air passageway and route the cooling air through the airfoil 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 being in fluid communication with the airfoil air passageway and being configured to discharge a second percentage of the cooling air,

the plurality of directional film holes including a first portion of film holes and a second portion of film holes,

the first portion of film holes being configured to discharge the cooling air toward the tip end at a first target angle relative to the platform, and

the second portion of film holes being configured to discharge the cooling air toward the root end at a second target angle relative to the platform, wherein

an upper portion of the plurality of trailing edge slots is configured to discharge the cooling air from the turbine blade upward at a first trailing edge angle relative to the platform,

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

the first target angle is substantially the same as the first trailing edge angle,

the second target angle is substantially the same as the second trailing edge angle,

the plurality of trailing edge slots includes 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 being configured to discharge the cooling air upward, downward, and in between;

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

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

6. The turbine blade of claim 5, wherein each film hole of the plurality of directional film holes is positioned downstream from the leading edge between sixty and ninety percent of a length from the leading edge to the trailing edge;

and

wherein each film hole of the plurality of directional film holes has a film hole discharge angle from the outer wall between 15 degrees and 45 degrees relative to a film transition line extending from the leading edge toward the trailing edge.

7. The turbine blade of claim 5, wherein the first portion of film holes extend from a film transition line as a first single-column spanwise array toward the tip end;

wherein the second portion of 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 film hole of the first portion of film holes is positioned on or between the film transition line and the platform; and

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

8. 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 being configured to receive cooling air from the cooling air inlet and route the cooling air through the base air passageway; 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 being configured to receive the cooling air from the base air passageway and route the cooling air through the airfoil 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 being in fluid communication with the airfoil air passageway and being configured to discharge a second percentage of the cooling air,

the plurality of directional film holes including a first portion of film holes and a second portion of film holes,

the first portion of film holes being configured to discharge the cooling air toward the tip end at a first target angle relative to the platform, and

the second portion of film holes being configured to discharge the cooling air toward the platform at a second target angle relative to the platform, wherein

an upper portion of the plurality of trailing edge slots is configured to discharge the cooling air from the turbine blade upward at a first trailing edge angle relative to the platform,

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

the first target angle is substantially the same as the first trailing edge angle,

the second target angle is substantially the same as the second trailing edge angle,

the plurality of trailing edge slots includes 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 being configured to discharge the cooling air upward, downward, and in between,

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

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

9. The turbine blade of claim 8, wherein each film hole of the plurality of directional film holes is positioned downstream from the leading edge between sixty and ninety percent of a length from the leading edge to the trailing edge.

10. The turbine blade of claim 8, wherein the first portion of 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 film holes extend 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.

11. The turbine blade of claim 10, wherein one of the first single-column spanwise array and the second single-column spanwise array is positioned upstream of the other;

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

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

12. The turbine blade of claim 8, wherein each film hole of the plurality of directional film holes has a film hole discharge angle from the outer wall between 15 degrees and 45 degrees relative to a film transition line extending from the leading edge toward the trailing edge.

13. The turbine blade of claim 8, wherein the first portion of film holes is further configured to discharge the cooling air upward at a first target angle between 10 degrees and 40 degrees in a positive direction toward the tip end;

and

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

14. The turbine blade of claim 8, wherein the first trailing edge angle is between 10 degrees and 40 degrees and the second trailing edge angle is between 10 degrees and 40 degrees.

15. A gas turbine engine including a turbine having a turbine rotor assembly that includes the turbine blade of claim 8, the turbine rotor assembly being installed in a first stage of the turbine.