Aero-mixing of rotating blade structures

• US 7,753,652 B2
• Filed: 12/15/2006
• Issued: 07/13/2010
• Est. Priority Date: 12/15/2006
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Gray, Lewis, Truckenmueller, Frank, Stueer, Heinrich, Martin, Harry F.
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): Ellis; Ryan H
• Application Number:
  US11/639,962
• Publication Number:
  US 20080145228A1
• Time in Patent Office: 1,306 Days
• Field of Search: 416/189, 416/203, 416/212.R, 416/212.A, 416/243, 416/DIG.5
• US Class Current: 416/189
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/142 of the blades of successive rotor or stator blade-rows
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F05D 2240/302 characteristics related to shock waves, transonic or supersonic flow
• CPC Class Codes: Y10S 416/05 Variable camber or chord length

Abstract

An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.

Claims

1. An array of flow directing elements for use in a turbomachine comprising:

a plurality of flow directing elements mounted on a rotor disk, each said flow directing element including a radially extending span dimension and a chord dimension extending substantially perpendicular to said span dimension;

said plurality of flow directing elements comprising first flow directing elements forming a first set of flow directing elements and second flow directing elements forming a second set of flow directing elements;

said flow directing elements each comprise a leading edge and a trailing edge, and said trailing edges of said second set of flow directing elements are located at a different axial location than corresponding trailing edges of said first set of flow directing elements to define different chordal dimensions for said second set of flow directing elements;

wherein an element-to-element flow field defined between successive ones of said first set of flow directing elements is interrupted by said second set of flow directing elements to form an asymmetric element-to-element flow field around said array of flow directing elements; and

wherein each of two or more of said flow directing elements have one or more respective coupling components, each said one or more coupling component having opposite front and rear contact surfaces with respect to a rotational direction of said rotor disk, said one or more coupling components being arranged in such a way that coupling components of two adjacent flow directing elements are brought into contact with each other at adjacent front and rear contact surfaces during rotation.

2. The array of claim 1, wherein said chord dimensions of said second set of flow directing elements differs from said chord dimensions of said first set of flow directing elements at corresponding span-wise locations, extending from a location beginning from about 60% to about 100% of the span of said flow directing elements.

3. The array of claim 1, wherein at least one of said second flow directing elements is located between a pair of said first flow directing elements.

4. The array of claim 3, wherein the trailing edge of said at least one second flow directing element is displaced axially forwardly from a line connecting the trailing edges of said pair of first flow directing elements.

5. The array of claim 4, wherein said trailing edge of said at least one second flow directing element is displaced axially forwardly a distance of up to about 8% of the chord length of said pair of first flow directing elements.

6. The array of claim 1, wherein said one or more coupling components comprises a shroud located at a radially outer end of each of said flow directing elements.

7. An array of flow directing elements for use in a turbomachine comprising:

a plurality of flow directing elements mounted to a rotor disk, each said flow directing element including a radially extending span dimension and a chord dimension extending from a leading edge to a trailing edge substantially perpendicular to said span dimension;

said plurality of flow directing elements comprising first flow directing elements forming a first set of flow directing elements and second flow directing elements forming a second set of flow directing elements;

wherein said second set of flow directing elements has a chord dimension defined by a value that is different than the value of a chord dimension measured at corresponding span-wise locations of said first set of flow directing elements such that the different chord dimensions between the first and second flow directing elements interrupts an element-to-element flow field defined between successive ones of said first set of flow directing elements at said trailing edge of said flow directing elements to form an asymmetric element-to-element flow field around said array of flow directing elements; and

wherein each of two or more of said flow directing elements have one or more respective coupling components, each said one or more coupling component having opposite front and rear contact surfaces with respect to a rotational direction of said rotor disk, said one or more coupling components being arranged in such a way that coupling components of two adjacent flow directing elements are brought into contact with each other at adjacent front and rear contact surfaces during rotation.

8. The array of claim 7, wherein said chord dimension of said second set of flow directing elements is shorter than the chord dimension of said first set of flow directing elements.

9. The array of claim 8, wherein said second flow directing elements are positioned alternately with said first flow directing elements around said rotor disk.

10. The array of claim 7, wherein said span dimension comprises an inner span region adjacent to said rotor disk and an outer span region spaced from said rotor disk, and points on said trailing edges of said second set of flow directing elements are located at different axial locations than points located at corresponding span-wise locations of said first set of flow directing elements beginning at said outer region and extending toward a tip of said flow directing elements.

11. The array of claim 10, wherein said points on said trailing edges of said second set of flow directing elements are displaced axially forwardly up to about 8% from points located at corresponding span-wise locations of said first set of flow directing elements.

12. The array of claim 11, wherein said points on said trailing edges of said second set of flow directing elements are displaced axially forwardly about 4% at a radial location of about 90% of the span length.

13. The array of claim 11, wherein said points on said trailing edges of said second set of flow directing elements are displaced axially forwardly about 8% at a radial location of from about 70% to about 80% of the span length.

14. An array of flow directing elements for use in a turbomachine to increase flutter stability comprising:

a plurality of flow directing elements mounted to a rotor disk, each said flow directing element including a radially extending span dimension and a chord dimension extending from a leading edge to a trailing edge substantially perpendicular to said span dimension;

said plurality of flow directing elements comprising first flow directing elements forming a first set of flow directing elements and second flow directing elements forming a second set of flow directing elements;

wherein a portion of said trailing edge of said second set of flow directing elements differs from a corresponding trailing edge portion of said first set of flow directing elements such that said second set of flow directing elements has a chord dimension defined by a value that is smaller than the value of a chord dimension measured at corresponding span-wise locations of said first set of flow directing elements to interrupt a shock field downstream of said flow directing elements and reduce shock induced flutter in said flow directing elements; and

wherein each of two or more of said flow directing elements have one or more respective coupling components, each said one or more coupling component having opposite front and rear contact surfaces with respect to a rotational direction of said rotor disk, said one or more coupling components being arranged in such a way that coupling components of two adjacent flow directing elements are brought into contact with each other at adjacent front and rear contact surfaces during rotation.

15. The array of claim 14, wherein said span dimension comprises an inner span region adjacent to said rotor disk and an outer span region spaced from said rotor disk, and points on said trailing edges of said second set of flow directing elements are located at axial locations that are displaced axially forwardly of points located at corresponding span-wise locations of said first set of flow directing elements beginning at said outer region and extending toward a tip of said flow directing elements.

16. The array of claim 15, wherein said second flow directing elements are positioned alternately with said first flow directing elements around said rotor disk.