BACKGROUND OF THE INVENTION
This disclosure relates generally to a gas turbine engine and more particularly to a gas turbine engine assembly that seals a gap between components thereof.
Components of a turbine engine may be used in conjunction to seal various components as part of a larger turbine engine system. For example, a Tangential On-Board Injector (“TOBI”) is a well know device, which may be known by different names, that is utilized to provide cooling air to the turbine section of the gas turbine engine. The TOBI receives air from a source of cooling air and passes it to the rotating turbine. The efficient use of the cooling air by the TOBI is important to provide cooling capacity to the engine, and to enhance engine performance.
A TOBI may be used in conjunction with a group of turbine vanes. However, using these or similar components can create gaps between the components.
SUMMARY OF THE INVENTION
A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system also includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending across the gap. The second portion of the first seal and the second portion of the second seal are adjacent and overlapping with each other to seal the gap.
A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system further includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending into the gap. The second portion of the first seal and the second portion of the second seal are parallel and overlapping with each other to seal the gap.
These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 shows a perspective view of the sealing system.
FIG. 2 shows a cross section of the sealing system, including both a first and second seal.
FIG. 3 shows a perspective view of the sealing system, including a first and second body.
FIG. 4 shows a cross section of the sealing system using a step configuration.
FIG. 5 shows a cross section of the sealing system using a slot configuration.
FIG. 6 shows a cross section of the sealing system using a slant configuration with a slot.
FIG. 7 shows a cross section of the sealing system using a slant configuration without a slot.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to FIG. 1, a sealing system 8 is shown. The sealing system 8 is located within a turbine engine, downstream of a compressor (not shown), and includes a first body 10, a second body 12, a first seal 14, and a second seal 16. As seen in FIG. 1, the first body 10 is continuous and the second body 12 is segmented such that the segments are joined to form a singular body. Alternatively, the first body 10 may be segmented and the second body 12 may be continuous, or both the first body 10 and second body 12 can be segmented. While not limiting, as shown in FIG. 1, the first body 10 is a TOBI and the second body 12 is a ring of turbine vanes.
The first body 10 includes a first seal 14, and the second body 12 includes a second seal 16. While not limiting, the seals 14, 16 can be made of a material such as AMS 5608 Cobalt, or similar material. Similarly, the first body 10 and second body 12 may be cylinders, such as a TOBI or ring of turbine vanes, and may be continuous or segmented.
The first seal 14, as shown, is a ring seal. The second seal 16, as shown, is a featherseal. Both the first seal 14 and second seal 16 are not limited to these types of seals, but are able to account for relative movement between the bodies caused by heating and cooling thereof. The seals 14, 16 may also expand at different rates relative to each other to account for differing thermal transients. The first seal 14, as shown in FIG. 1, has a smaller diameter than the first body 10 and sits within the first body 10. The first seal 14 is inserted by slightly contracting, or otherwise forcing the seal 14 such that it will fit onto the first body 10. It is, at least in part, held in place within the first body 10 by slight interference loading between the first body 10 and the first seal 14, causing it to create a seal with the contacting portion of the first body 10. The interference loading occurs from contact between the first seal 14 and first body 10. Both the first seal 14 and second seal 16 may be removable to allow for a replacement seals 14, 16 when necessary.
Referring to FIG. 2, the second seal 16 sits within the second body 12. The second seal 16 is used to seal circumstantial gaps between adjacent second bodies 12. The second seal 16 is bent such that it is able to occupy both a vertical and horizontal position within the second body 12. The second seal 16 is inserted into the second body 12 and shaped such that a second section 19 extends in a generally vertical direction relative to a third seal 18, which extends in a relatively horizontal direction. The angle between the first section 17 and the third seal 18 is sufficient that the second seal 16 cannot escape out of the slot retaining the first seal 14. In one non-limiting example, the second seal is 16 a featherseal and includes a bend of about 90°. Pressure within the second body 12 from a pressure differential between the high pressure area 20 and the low pressure area 22 pushes the seal 16 in an upward direction at section 17, and in conjunction with third seal 18 back against the outer wall relative to a high pressure side 20. This forces the second seal 16 against the second body 12. The second seal 16 is inserted into the second body 12 without further means of connection to the second body 12.
Referring to FIG. 3, there is a gap 34, which exists between the first body 10 and second body 12 and allows cooling air from the high pressure side 20 to escape the system 8. At least a first portion 30 of the first seal 14 and a first portion 32 of the second seal 16 are aligned parallel to one another and are overlapping vertically within the gap 34. The first seal 14 and second seal 16 are aligned to seal the gap 34, as well as effectively limiting any gaps 34 at the first portion 30 of the first seal 14 and the first portion 32 of the second seal 16. By sealing the gap 34, air used by the system 8 and found in the high pressure side 20 is prevented from leaving the system 8, as it can no longer escape through the gap 34. The first seal 14 and second seal 16 are held in a relatively fixed position and pushed together because of the pressure differential existing between a high pressure side 20 and a low pressure side 22. The pressure differential causes the seals 14,16 to move together to reduce any amount of significant gaps between the seals 14,16 as well as to seal the gap 34. Higher pressure air comes from the air compressor discharge (not shown) from a turbine engine to create the high pressure side 20.
Referring to FIG. 4, a sealing system 8 includes a first body 110 and second body 112. A first seal 114 and second seal 116 are further included, with the first seal 114 contacting the first body 110 and a second seal 116 contacting the second body 112. There is also a gap 134, which exists between the first body 110 and second body 112, that allows cooling air from the high pressure side 120 to escape the system 8. A first portion 130 of the first seal 114 is parallel to and overlapping a first portion 132 of the second seal 116. A second portion 136 of the first seal 114 is also shown. The gap 134 is sealed such that at least a portion of the gap 134 is located between the first portion 130 and second portion 136 of the first seal 114. By sealing the gap 134, air used by the system 8 and found in the high pressure side 120 is prevented from leaving the system 8, as it can no longer escape through the gap 134. The first seal 114 and second seal 116 are held in a relatively fixed position and pushed together because of the pressure differential existing between a high pressure side 120 and a low pressure side 122. The pressure differential causes the seals 114, 116 to move together to reduce any amount of significant gaps between the seals 114, 116 as well as to seal the gap 134. Higher pressure air comes from the air compressor discharge (not shown) from a turbine engine to create the high pressure side 120.
Referring to FIG. 5, a sealing system 8 includes a first body 210 and second body 212. A first seal 214 and second seal 216 are also shown, with the first seal 214 at least partially contacting the first body 210 and the second seal 216 at least partially contacting the second body 212. There is also a gap 234, which exists between the first body 210 and second body 212 and allows cooling air from the high pressure side 220 to escape the system 8. A first portion 230 of the first seal 214 is parallel to and overlapping a first portion 232 of the second seal 216. A second portion 236 of the first seal 214 is also shown. The second portion 236 sits within a slot 240 created within the first body 210. The gap 234 is sealed such that at least a portion of the gap 234 sits between the first portion 230 and second portion 236 of the first seal 214. By sealing the gap 234, air used by the system 8 and found in the high pressure side 220 is prevented from leaving the system 8, as it can no longer escape through the gap 234. The first seal 214 and second seal 216 are held in a relatively fixed position and pushed together because of the pressure differential existing between a high pressure side 220 and a low pressure side 222. The pressure differential causes the seals 214, 216 to move together to reduce any amount of significant gaps between the seals 214, 216 as well as to seal the gap 234. Higher pressure air comes from the air compressor discharge (not shown) from a turbine engine to create the high pressure side 220.
Referring to FIGS. 6 and 7, a sealing system 8 includes a first body 310 and second body 312. A first seal 314 is in contact with the first body 310, and a second seal 316 is in contact with the second body 312. Alternatively, a first section 330 of the first seal 314 can sit in a slot 342 of the first body 310. The first seal 314 may sit within a slot 342 of the first body 310. There is also a gap 334, which exists between the first body 310 and second body 312 and allows cooling air from the high pressure side 320 to escape the system 8. A first portion 330 of the first seal 314 is adjacent to a first portion 332 of the second seal 316. The first portion 330 of the first seal 314 and first portion 332 of the second seal 316 at least partially overlap relative to each other. The combination of the first seal 314 and second seal 316 seal the gap 334, preventing any cooling air present in the high pressure side 320 from flowing out of the system through the gap 34 towards a low pressure side 322. Alternatively, the gap 334 can sit between a second portion 340 and the first portion 330 of the first seal 314. The first seal 314 and second seal 316 are held in a relatively fixed position due to pressure as well as interference loading. Pressure results from the flow of air compressor discharge (not shown) from a turbine engine into a high pressure side 320. The pressure differential between the high pressure side 320 and the low pressure side 322 causes the seals 314, 316 to move together to reduce any amount of significant gaps between the seals 314, 316 as well as to seal the gap 334. Here, due to the angle of the first seal 314 within the system 8, the first seal 314 seals at the first body 310 more efficiently due to the increased pressure loading across the seal 314. This accounts for less of the first portion 330 of the first seal 314 being in registration with the first portion 332 of the second seal 316
Although a preferred embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Patent Grant
8794640
