TURBINE SLOTTED ARCUATE LEAF SEAL

• US 20170107837A1
• Filed: 10/20/2015
• Published: 04/20/2017
• Est. Priority Date: 10/20/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Gallier, Kirk Douglas, Andrews, Timothy Francis, Huizenga, Benjamin Scott, Feldmann, Kevin Robert, Frederick, Robert Alan, Groves, II, Robert Charles, Senile, Darrell
• Granted Patent: US 10,161,257 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F01D 9/047 Nozzle boxes
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/57 Leaf seals
• CPC Class Codes: F05D 2250/71 curved
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: F16J 15/061 with positioning means F16J15/0831 takes precedence
• CPC Class Codes: F16J 15/0887 the sealing effect being obtained by elastic deformation of the packing
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.

Claims

1. A gas turbine engine arcuate leaf seal assembly comprising:

an arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components,

the leaf seal operable for preventing or inhibiting leakage between first and second fluid volumes through a gap between the first and second turbine components, and

upper and lower leaf seal portions of the arcuate leaf seal disposed in radially spaced apart arcuate leaf seal upper and lower grooves in the first and second turbine components respectfully.

2. The assembly as claimed in claim 1, further comprising the leaf seal including an arcuate body and at least one circumferential retention tab extending radially away from the arcuate body.

3. The assembly as claimed in claim 2, further comprising the retention tab disposed in a notch in a forward or aft annular wall or an aft annular wall of the upper or lower grooves.

4. The assembly as claimed in claim 3, further comprising the retention tab being sufficiently flexible for the leaf seal to engage seal edges on upper and lower faces of the upper and lower grooves respectively during entire range of engine operation.

5. The assembly as claimed in claim 3, further comprising the leaf seal having a thickness in a range of from 3 mils to 35 mils.

6. The assembly as claimed in claim 3, further comprising the leaf seal made of a material with torsional stiffness in a range between 0.015 lb/in and 0.15 lb/in.

7. The assembly as claimed in claim 1, further comprising the adjacent first and second turbine components being radially adjacent turbine nozzle upper and lower components respectively or the adjacent first and second turbine components being axially adjacent.

8. The assembly as claimed in claim 7, further comprising one of the turbine nozzle upper and lower components includes a ceramic matrix composite material.

9. A segmented turbine nozzle comprising:

a ring of turbine nozzle segments circumscribed about an axis;

each of the turbine nozzle segments includes a radially inner support ring segment, a radially outer support ring segment, and at least one nozzle fairing supported and disposed therebetween;

radially spaced apart inner and outer band segments of the nozzle fairing and a hollow fairing airfoil extending radially therebetween;

a strut radially disposed through the hollow fairing airfoil and coupled to and operable for carrying load between the inner and outer support ring segments;

at least one gas turbine engine arcuate leaf seal assembly including an arcuate leaf seal extending radially and circumferentially between the inner band segment and the inner support ring segment; and

upper and lower leaf seal portions of the arcuate leaf seal disposed in radially spaced apart arcuate leaf seal upper and lower grooves in the inner band segment and the inner support ring segment respectfully.

10. The turbine nozzle as claimed in claim 9, further comprising:

forward and aft turbine leaf seal assemblies including the at least one gas turbine engine arcuate leaf seal assembly,

the forward and aft turbine leaf seal assemblies positioned at forward and aft ends of the nozzle segment respectfully between the inner support ring segment and the inner band segment of the fairing,

each of the forward and aft turbine leaf seal assemblies including an arcuate leaf seal extending radially and circumferentially between the inner band segment and the inner support ring segment,

each of the forward and aft turbine leaf seal assemblies including radially spaced apart arcuate leaf seal upper and lower grooves in upper and lower flanges of the inner band segment and the inner support ring segment respectively, and

upper and lower leaf seal portions of each of the arcuate leaf seals of each of the forward and aft turbine leaf seal assemblies disposed in the radially spaced apart arcuate leaf seal upper and lower grooves in the inner band segment and the inner support ring segment respectfully.

11. The turbine nozzle as claimed in claim 10, further comprising each of the leaf seals including an arcuate body and at least one circumferential retention tab extending radially away from the arcuate body.

12. The turbine nozzle as claimed in claim 11, further comprising the retention tab disposed in a notch in a forward or aft annular wall or an aft annular wall of each of the upper or lower grooves and the retention tab being sufficiently flexible for the leaf seal to engage seal edges on upper and lower faces of each of the upper and lower grooves respectively during engine operation over entire range of engine operation.

13. The turbine nozzle as claimed in claim 12, further comprising each of the leaf seals having a thickness in a range of from 3 mils to 35 mils.

14. The turbine nozzle as claimed in claim 12, further comprising each of the leaf seals made of a material with torsional stiffness in a range between 0.015 lb/in and 0.15 lb/in.

15. The turbine nozzle as claimed in claim 12, further comprising one of the inner band segment and the inner support ring segment including a ceramic matrix composite material.

16. The turbine nozzle as claimed in claim 12, further comprising the at least one nozzle fairing made of a ceramic matrix composite material.

17. The turbine nozzle as claimed in claim 10, further comprising an annular cooling air plenum including flow cavities disposed in the inner support ring segments and in flow communication with the hollow fairing airfoils.

18. The turbine nozzle as claimed in claim 17, further comprising:

each of the leaf seals including an arcuate body and at least one circumferential retention tab extending radially away from the arcuate body,

the retention tab disposed in a notch in a forward or aft annular wall or an aft annular wall of each of the upper or lower grooves, and

the retention tab being sufficiently flexible for the leaf seal to engage seal edges on upper and lower faces of each of the upper and lower grooves respectively during engine operation over entire range of engine operation.

19. The turbine nozzle as claimed in claim 18, further comprising each of the leaf seals having a thickness in a range of from 3 mils to 35 mils and/or each of the leaf seals made of a material with torsional stiffness in a range between 0.015 lb/in and 0.15 lb/in.

20. The turbine nozzle as claimed in claim 12, further comprising:

the annular cooling air plenum including spline seals sealingly disposed between circumferentially adjoining ones of the turbine nozzle segments;

the spline seals disposed in spline seal slots; and

the spline seal slots including axially extending upper slots disposed in the inner band segments of the nozzle fairings, axially extending lower slots disposed in the inner support ring segments, radially extending forward and aft slots disposed in the upper and lower flanges of the inner band segment and the inner support ring segment respectively.