Impingement jet strike channel system within internal cooling systems

• US 10,408,064 B2
• Filed: 07/09/2014
• Issued: 09/10/2019
• Est. Priority Date: 07/09/2014
• Status: Active Grant

• Current Assignee: Siemens Energy Global GmbH & Co. KG (Siemens AG)
• Original Assignee: Siemens AG
• Inventors: Zuniga, Humberto A.
• Primary Examiner(s): Malik, Raheena R
• Application Number:
  US15/317,982
• Publication Number:
  US 20180258773A1
• Time in Patent Office: 1,889 Days
• Field of Search: 165 41
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2250/32 according to their shape
• CPC Class Codes: F05D 2250/711 convex
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: F28F 13/12 by creating turbulence, e.g. by stirring, by increasing the force of circulation F28F13/08 takes precedence
• CPC Class Codes: F28F 2210/02 with particular branching, e.g. fractal conduit arrangements

Abstract

An internal cooling system (14) including an impingement jet strike channel system (16) for increasing the effectiveness of impingement jets (18) is disclosed. The impingement jet strike channel system (16) may include an impingement jet strike cavity (20) offset from one or more impingement orifices (22). A plurality of impingement jet strike channels (24) may extend radially outward from the impingement jet strike cavity (20) forming a starburst pattern of impingement jet strike channels (24) and may be formed by a plurality of ribs (26) that each separate adjacent impingement jet strike channels (24). The ribs (26) forming the impingement jet strike channels (24) may be split one or more times into multiple channels to increase the number of stagnation points (28, 38, 52) to increase the cooling capacity. The impingement jet strike channel system (16) may be used within components, such as, but not limited to, gas turbine engines (12), including vane inserts, airfoil leading edge cooling systems, platforms, advanced transitions, acoustic resonators, ring segments and the like.

Claims

1. An internal cooling system comprising:

at least one impingement jet strike channel system, comprising;

an impingement jet strike cavity offset from at least one impingement orifice, wherein the impingement jet strike cavity is defined by surfaces on at least three sides and includes an opening facing the at least one impingement orifice;

a plurality of impingement jet strike channels extending radially outward from the impingement jet strike cavity and formed by a plurality of ribs that each separate adjacent impingement jet strike channels; and

wherein at least one of the plurality of impingement jet strike channels is divided into first sub-jet strike channels extending radially outward of an inlet of the impingement jet strike channel from a stagnation point created in the impingement jet strike channel at an upstream end of a first sub-rib,

wherein at least one of the plurality of impingement jet strike channels increases in depth from an outer surface of the ribs to an inner surface of impingement jet strike channel when moving radially outward from the impingement jet strike cavity.

2. The internal cooling system of claim 1, wherein each of the plurality of impingement jet strike channels is divided into first sub-jet strike channels extending radially outward of an inlet of the impingement jet strike channel from a stagnation point created in the impingement jet strike channel at an upstream end of a first sub-rib.

3. The internal cooling system of claim 2, wherein the first sub-jet strike channels are narrower in width than the impingement jet strike channels.

4. The internal cooling system of claim 2, wherein at least one of the first sub-jet strike channels is divided into second sub-jet strike channels extending radially outward of the upstream end of a first sub-rib from a stagnation point created in the first sub-jet strike channel at an upstream end of a second sub-rib.

5. The internal cooling system of claim 4, wherein at least one of the second sub-jet strike channels is divided into third sub-jet strike channels extending radially outward of the upstream end of a second sub-rib from a stagnation point created in the second sub-jet strike channel at an upstream end of a third sub-rib.

6. The internal cooling system of claim 1, wherein each of the first sub-jet strike channels is divided into second sub-jet strike channels extending radially outward of the upstream end of a first sub-rib from a stagnation point created in the first sub-jet strike channel at an upstream end of a second sub-rib.

7. The internal cooling system of claim 6, wherein each of the second sub-jet strike channels is divided into third sub-jet strike channels extending radially outward of the upstream end of a second sub-rib from a stagnation point created in the second sub-jet strike channel at an upstream end of a third sub-rib.

8. The internal cooling system of claim 1, wherein adjacent first sub-jet strike channels merge together radially outward from the upstream end of the first sub-rib.

9. The internal cooling system of claim 1, wherein the plurality of impingement jet strike channels are defined by surfaces on at least three sides and includes an opening facing the at least one impingement orifice.

10. The internal cooling system of claim 1, wherein the plurality of impingement jet strike channels extending radially outward from the impingement jet strike cavity forms a starburst pattern of impingement jet strike channels.

11. The internal cooling system of claim 1, wherein the plurality of impingement jet strike channels are formed from a plurality of ribs extending radially outward from a surface forming a portion of the internal cooling system.

12. The internal cooling system of claim 1, wherein the plurality of impingement jet strike channels are formed by the plurality of impingement jet strike channels being positioned within a surface forming a portion of the internal cooling system.

13. The internal cooling system of claim 1, wherein at least one side surface forming at least one of the plurality of impingement jet strike channels is non-linear.

14. The internal cooling system of claim 1, wherein at least one of the ribs forming the impingement jet strike channels has a narrower base than a top, which directs impingement cooling fluids inward toward a surface from which the impingement jet strike channels extend.

15. The internal cooling system of claim 1, wherein the ribs forming the plurality of impingement jet strike channels are petal shaped with pointed upstream and downstream ends connected with convex first and second sides.

16. The internal cooling system of claim 13, wherein the at least one side surface includes a concave section and a convex section, the convex section being positioned outward of the concave section from an inner surface of the impingement jet strike channel.