초록 ▼

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 seco

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 respectively. 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.

대표청구항 ▼

1. 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;radia

1. 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; andupper 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 respectively. 2. The turbine nozzle as claimed in claim 1, 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 respectively 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, andupper 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 respectively. 3. The turbine nozzle as claimed in claim 2, 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. 4. The turbine nozzle as claimed in claim 3, further comprising each 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 each 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. 5. The turbine nozzle as claimed in claim 4, further comprising each of the leaf seals having a thickness in a range of from 3 mils to 35 mils. 6. The turbine nozzle as claimed in claim 4, 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. 7. The turbine nozzle as claimed in claim 4, further comprising one of the inner band segment and the inner support ring segment including a ceramic matrix composite material. 8. The turbine nozzle as claimed in claim 4, further comprising the at least one nozzle fairing made of a ceramic matrix composite material. 9. The turbine nozzle as claimed in claim 2, 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. 10. The turbine nozzle as claimed in claim 9, 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, andthe 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. 11. The turbine nozzle as claimed in claim 10, 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. 12. The turbine nozzle as claimed in claim 4, 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; andthe 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.