Gas turbine: seal between adjacent can annular combustors
First Claim
1. A seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater, comprising:
- a plate configured to extend between adjacent transition sections, wherein the plate has at least one perforation extending from a front surface of the plate to a rear surface of the plate;
a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix is fixedly attached to a surface of the plate; and
wherein the porous matrix comprises a fibrous hose and a fibrous packing material, wherein the fibrous packing material comprises the portion of the porous matrix fixedly attached to a surface of the plate and wherein the plate and the fibrous packing material attached thereto are disposed within the fibrous hose.
2 Assignments
0 Petitions
Accused Products
Abstract
The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate.
34 Citations
18 Claims
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1. A seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater, comprising:
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a plate configured to extend between adjacent transition sections, wherein the plate has at least one perforation extending from a front surface of the plate to a rear surface of the plate; a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix is fixedly attached to a surface of the plate; and wherein the porous matrix comprises a fibrous hose and a fibrous packing material, wherein the fibrous packing material comprises the portion of the porous matrix fixedly attached to a surface of the plate and wherein the plate and the fibrous packing material attached thereto are disposed within the fibrous hose. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A turbine engine, comprising:
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a plurality of adjacent can annular combustors extending generally axially and each having a transition section, wherein a portion of the transition sections are positioned proximate to each other creating radially extending gaps; wherein at least one pair of transition sections each includes a radially extending channel in a side surface defining a portion of the radially extending gap between two transition sections; wherein the channels in the transition sections are generally aligned to create a radially-oriented seal housing; and a seal comprising a plate configured to extend between adjacent transition sections, wherein the plate has at least one perforation extending from a front surface of the plate to a rear surface of the plate, and a porous matrix formed from materials ca able of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix is fixedly attached to a surface of the plate, wherein the porous matrix comprises a fibrous hose and a fibrous packing material, wherein the fibrous packing material comprises the portion of the porous matrix fixedly attached to a surface of the plate and wherein the plate and the fibrous packing material attached thereto are disposed within the fibrous hose. - View Dependent Claims (16, 17, 18)
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Specification