Turbine engine ring seal

• US 7,726,936 B2
• Filed: 07/25/2006
• Issued: 06/01/2010
• Est. Priority Date: 07/25/2006
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Keller, Douglas A., Campbell, Christian X., Vance, Steven J.
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): White; Dwayne J
• Application Number:
  US11/492,590
• Publication Number:
  US 20100104426A1
• Time in Patent Office: 1,407 Days
• Field of Search: 415/173.5, 415/171.1, 415/173.1, 415/173.3, 415/173.4, 415/173.6, 415/174.1, 415/174.2, 415/174.3, 415/214.1, 415/215.1, 415/134, 415/135, 415/139, 416/244.R
• US Class Current: 415/173.4
• CPC Class Codes: F01D 11/12 using a rubstrip, e.g. erodible. deformable or resiliently-biased part
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/11 Shroud seal segments

Abstract

Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine.

Claims

1. A turbine engine ring seal segment comprising:

a first channel having a radially inwardly concave surface, the first channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction, wherein the extension of the first channel includes an outer surface that is exposed to turbine blades in use;

a separate second channel having a radially inwardly concave surface, the second channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction, wherein the extension of the second channel includes an outer surface that is exposed to turbine blades in use, the first and second channels being detachably coupled such that the aft span of the first channel substantially abuts the forward span of the second channel so as to define an axial interface and the extensions for the first and second channels form a uninterrupted planar surface across the entirety of the extensions; and

at least one of a seal and a bonding material operatively engaging the aft span of the first channel and the forward span of the second channel.

2. The turbine engine ring seal segment of claim 1 wherein at least one of the first and second channels is made of ceramic matrix composite.

3. The turbine engine ring seal segment of claim 1 wherein each channel includes a transition region between each of the forward and aft spans and the axial extension, wherein at least one of the first and second channels is preloaded, whereby at least a portion of each of the transition regions is placed in compression in the through thickness direction.

4. The turbine engine ring seal segment of claim 1 wherein at least one of the channels is made of a material other than a ceramic matrix composite.

5. The turbine engine ring seal segment of claim 1 wherein the first and second channels are made of different materials.

6. The turbine engine ring seal segment of claim 1 wherein each of the channels includes an inner surface and an outer surface, wherein at least the inner surface of the extension of at least one of the channels is coated with a thermal insulating material.

7. The turbine engine ring seal segment of claim 6 wherein the thickness of the thermal insulating material decreases along the extension in the axial direction.

8. The turbine engine ring seal segment of claim 1 further including a plurality of fasteners, wherein each fastener operatively engages the aft span of the first channel and the forward span of the second channel such that the first and second channels are detachably coupled.

9. A turbine engine ring seal system comprising:

a turbine stationary support structure; and

a first ring seal segment operatively connected to the turbine stationary support structure, the ring seal segment including a first channel and a separate second channel,

the first channel having a radially inwardly concave surface, the first channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction;

the second channel having a radially inwardly concave surface, the second channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction, the first and second channels being detachably coupled such that the aft span of the first channel substantially abuts the forward span of the second channel, thereby defining an axial interface; and

at least one seal operatively engaging the aft span of the first channel and the forward span of the second channel such that the axial interface is substantially sealed, whereby coolant leakage through the axial interface is minimized;

a second ring seal segment including a first channel and a separate second channel,

the first channel having a radially inwardly concave surface, the first channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction,

the second channel having a radially inwardly concave surface, the first channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction, the first and second channels being detachably coupled such that the aft span of the first channel substantially abuts the forward span of the second channel, thereby defining an axial interface,

wherein each of the first and second ring seal segments includes opposite circumferential ends, and wherein one of the circumferential ends of the first ring seal segment substantially abuts one of the circumferential ends of the second ring seal segment to thereby define a circumferential interface; and

at least one seal operatively engaging the circumferential ends of the first and second ring seal segments that form the circumferential interface such that the circumferential interface is substantially sealed, whereby coolant leakage through the circumferential interface is minimized.

10. The turbine engine ring seal system of claim 9 wherein the first ring seal segment is operatively connected to the stationary support structure by a plurality of fasteners.

11. The turbine engine ring seal system of claim 9 wherein at least one of the first and second channels is made of ceramic matrix composite.

12. The turbine engine ring seal system of claim 9 wherein the first and second channels are made of different materials.

13. The turbine engine ring seal system of claim 9 wherein each of the channels includes an inner surface and an outer surface, wherein at least the inner surface of the extension of at least one of the channels is coated with a thermal insulating material.

14. The turbine engine ring seal segment of claim 9 wherein each channel includes a transition region between each of the forward and aft spans and the axial extension, wherein at least one of the first and second channels is preloaded, whereby at least a portion of each of the transition regions is placed in compression in the through thickness direction.

15. The turbine engine ring seal system of claim 9 wherein each of the channels includes an outer surface, and further including at least one seal attached to the outer surface of the first channel of the first ring seal segment so as to extend circumferentially beyond one of the circumferential ends of the first ring seal segment and into engagement with the outer surface of the first channel of the second ring seal segment, whereby the circumferential interface is substantially sealed.

16. The turbine engine ring seal segment of claim 15 further including a plurality of fasteners, wherein each fastener operatively engages the aft span of the first channel and the forward span of the second channel such that the first and second channels are detachably coupled.