Turbine engine with a blade

Patent metadata

Field	Value
Publication number	US-11927111-B2
Application number	US-202217836023-A
Country	US
Kind code	B2
Filing date	Jun 9, 2022
Priority date	Jun 9, 2022
Publication date	Mar 12, 2024
Grant date	Mar 12, 2024

Abstract

A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.

First claim

What is claimed is:

1. A component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow, comprising:
a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow; and
a set of cooling holes, each cooling hole of the set of cooling holes comprising a passage extending between an inlet at the cooled surface and an outlet at the heated surface, the passage defining a centerline forming a first angle (θ) with the heated surface, the passage having a top wall and a bottom wall each extending from the inlet toward the outlet, and a layback surface defining at least a portion of the outlet, extending from the bottom wall to the heated surface, the layback surface forming a second angle (β) with the bottom wall and a third angle (Δ) with the heated surface;
wherein for any range of angle values (α): (α low <α<α hi ):
for at least a first cooling hole of the set of cooling holes α hi +α low <θ, and α low <Δ<α hi ; and
for at least a second cooling hole of the set of cooling holes α hi +α low >θ, and α low <β<α hi .

2. The component of claim 1 wherein the range of angle values is 12°<α<16°.

3. The component of claim 1 wherein the range of angle values is 10°<α<20°.

4. The component of claim 1 wherein the range of angle values is 5°<α<40°.

5. The component of claim 1 wherein the layback surface intersects the heated surface at a downstream end of the outlet, the top wall intersects the heated surface at an upstream end of the outlet and a straight-line distance measured from the downstream end to the upstream end defines a first dimension of the outlet.

6. The component of claim 5 wherein the set of cooling holes includes multiple cooling holes with each cooling hole having first dimensions within 5% of each other cooling hole.

7. The component of claim 1 wherein the second angle (β) and the third angle (Δ) have an interdependent relationship.

8. The component of claim 7 wherein as the first angle (θ) increases to a switch value (θ s ), one of the second angle (β) or the third angle (Δ) increases at a first rate while the other of the second angle (β) or the third angle (Δ) remains constant.

9. The component of claim 8 wherein as the first angle (θ) increases above the switch value (θ s ), the other of the second angle (β) and the third angle (Δ) increases at the first rate while the other of the second angle (β) and the third angle (Δ) remains constant.

10. The component of claim 1 located within a turbine engine, comprising:
an engine core extending along an engine centerline and including a compressor section, a combustor, and a turbine section in axial flow arrangement and defining a flow path;
a temperature sensor within the engine and configured to detect an exhaust gas temperature (EGT) within the engine core;
a set of nozzles circumferentially arranged in the turbine section and defining a number of nozzles (NN); and
a set of blades circumferentially arranged in the turbine section adjacent to, and downstream of, the set of nozzles, the set of blades defining a number of blades (NB);
wherein a blade in the set of blades comprises:
an outer wall bounding an interior and having an exterior surface, with the outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a chord-wise direction, and also extending between a tip and a root to define a span-wise direction;
a cooling conduit within the interior;
a tip radius (TR) defined between the engine centerline and the tip under standard day conditions of 15° C. at mean sea level altitude and 101.3 kPa atmospheric pressure;
a radial length (R) defined by a span-wise line extending between a first location on the outer wall and a second location on the outer wall, with the first location and the second location having a common chord-wise position;
a surface length (L max ) defined by a contour line along the outer wall between the first location and the second location at the common chord-wise position; and
a blade parameter (BP) defined as a ratio of the surface length to the radial length (BP=L max /R);
wherein the exhaust gas temperature EGT, the number of blades NB, the number of nozzles NN, the tip radius TR, and the blade parameter BP define a blade tip durability factor (BTDF) by the following expression:

BTDF
=

(

TR
EGT

)

×

(

NB
NN

)

×
BP

;

wherein the blade tip durability factor BTDF is between 0.020 and 0.033 in/° C., and the blade parameter BP is between 1-1.234.

11. A blade for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow, comprising:
a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow; and
a plurality of cooling holes each comprising a passage extending between an inlet at the cooled surface and an outlet at the heated surface, the outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a straight-line distance, the passage defining a centerline forming a first angle (θ) with the heated surface, a top wall, and a bottom wall each extending from the inlet toward the outlet, and a layback surface defining at least a portion of the outlet, extending from the bottom wall to the heated surface, the layback surface forming a second angle (β) with the bottom wall and a third angle (Δ) with the heated surface, wherein for any range of angle values (α): (α low <α<α hi ):
for at least a first cooling hole of the plurality of cooling holes α hi +α low <θ, and α low <Δ<α hi , and
for at least a second cooling hole of the plurality of cooling holes α hi +α low >θ, and α low <β<α hi ;

wherein the distances for each of the plurality of cooling holes is maintained within 5% of each other as the first angle (θ) increases regardless of the location of the cooling hole on the blade.

12. The blade of claim 11 wherein the range of angle values is 12°<α<16°.

13. The blade of claim 11 wherein the range of angle values is 10°<α<20°.

14. The blade of claim 11 wherein the range of angle values is 5°<α<40°.

15. The blade of claim 11 wherein as the first angle (θ) increases to a switch value (θ s ) one of the second angle (β) and the third angle (Δ) increases at a first rate while the other of the second angle (β) and the third angle (Δ) remains constant.

16. The blade of claim 15 wherein as the first angle (θ) increases above the switch value (θ s ) the other of the second angle (β) and the third angle (Δ) increases at the first rate while the other of the second angle (β) and the third angle (Δ) remains constant.

17. The blade of claim 11 wherein the layback surface intersects the bottom wall at a junction and a len

Assignees

• Gen Electric

Inventors

• Rausch Jonathan Michael
• Webster Zachary Daniel
• Feldmann Kevin Robert
• Perry Andrew David
• Gallier Kirk Douglas
• Osgood Daniel Endecott

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2220/32

  in gas turbines · CPC title

• 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