Turbine Engine Cold Section Vane Stage
AssigneeRtx Corporation
InventorsAndrew Carl Black, Bradley Paul Kline, Stephen H. Mattia, Jacob Kyle Yochimowitz
Life of this patent
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Abstract
A gas turbine engine stator stage has: a case; a plurality of vane clusters; and a plurality of vane singlets. The plurality of vane clusters each have: an inner diameter first platform; an outer diameter first shroud mounted to the case; and a plurality of first airfoils extending between the first platform and first shroud. The plurality of vane singlets each have: an inner diameter second platform; an outer diameter second shroud; and a single second airfoil extending between the second platform and second shroud.
Claims23
A gas turbine engine stator stage comprising:
- a case;
- a plurality of vane clusters each having:
- an inner diameter first platform;
- an outer diameter first shroud mounted to the case;
- and
- a plurality of first airfoils extending between the first platform and first shroud;
- and
- a plurality of vane singlets each having:
- an inner diameter second platform;
- an outer diameter second shroud;
- and
- a single second airfoil extending between the second platform and second shroud, wherein:
- the vane clusters are each a majority, by-weight, non-metallic;
- and
- the singlets are each, by-weight, a majority metallic.
(canceled)
A gas turbine engine stator stage comprising:
- a plurality of vane clusters each having:
- an inner diameter first platform;
- an outer diameter first shroud;
- and
- a plurality of first airfoils extending between the first platform and first shroud;
- and
- a plurality of vane singlets each having:
- an inner diameter second platform;
- an outer diameter second shroud;
- and
- a second airfoil extending between the second platform and second shroud, wherein:
- no two of the singlets are adjacent;
- the vane clusters are each a majority, by-weight, non-metallic;
- the singlets are each, by-weight, a majority metallic;
- the first platforms have first circumferential end sections and second circumferential end sections;
- the second platforms have first circumferential end sections and second circumferential end sections;
- and
- the second end sections of the first platforms and second platforms are dimensioned to be received in the first end sections of the first platforms and the second platforms respectively.
(canceled)
(canceled)
A gas turbine engine stator stage comprising:
- a case;
- a plurality of vane clusters each having:
- an inner diameter first platform;
- an outer diameter first shroud mounted to the case;
- and
- a plurality of first airfoils extending between the first platform and first shroud;
- and
- a plurality of vane singlets each having:
- an inner diameter second platform;
- an outer diameter second shroud;
- and
- a single second airfoil extending between the second platform and second shroud, wherein:
- at least one of the singlets includes measuring features not present in any of the doublets.
Dependencies are inferred from the claim text.