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A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The spar has a first chamber essentially along the suction side and a second chamber along the pressure side opposite the f

A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The spar has a first chamber essentially along the suction side and a second chamber along the pressure side opposite the first chamber.

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What is claimed is: 1. A vane comprising: an airfoil shell comprising a ceramic matrix composite and having: a leading edge; a trailing edge; a pressure side; and a suction side; a metallic spar within the shell; an outboard shroud at an outboard end of the shell; and an inboard platform at an inb

What is claimed is: 1. A vane comprising: an airfoil shell comprising a ceramic matrix composite and having: a leading edge; a trailing edge; a pressure side; and a suction side; a metallic spar within the shell; an outboard shroud at an outboard end of the shell; and an inboard platform at an inboard end of the shell, wherein the spar comprises: a first chamber essentially along the suction side; and a second chamber along the pressure side opposite the first chamber. 2. The vane of claim 1 wherein: the airfoil shell consists essentially of said ceramic matrix composite; the spar consists essentially of a first metallic casting; the platform consists essentially of a second metallic casting; and the shroud consists essentially of a third metallic casting. 3. The vane of claim 1 wherein: the spar comprises a sidewall having: a leading edge; a trailing edge; a pressure side; and a suction side; and the shell lacks tensile webs connecting the shell pressure and suction sides. 4. The vane of claim 1 wherein: the spar comprises a sidewall having: a leading edge; a trailing edge; a pressure side; and a suction side; and the spar first chamber is formed by a wall extending from proximate the spar leading edge to the spar sidewall at the suction side. 5. The vane of claim 1 further comprising: a plurality of seals between the shell and spar. 6. The vane of claim 5 wherein: the plurality of seals comprise at least one of ceramic rope seals and metallic bellows seals. 7. The vane of claim 5 wherein: the plurality of seals include first and second seals defining a cavity starting along the suction side downstream of the leading edge and ending at the trailing edge or along the suction side upstream of the trailing edge. 8. A method of manufacturing the vane of claim 1 comprising: casting the shroud; casting the platform; casting the spar; and ceramic matrix infiltration of a ceramic fiber preform to form the shell. 9. The method of claim 8 wherein: a plurality of spanwise seals are positioned between the spar and shell. 10. A method of cooling the vane of claim 1 comprising: directing a first airflow to the first chamber; and directing a second airflow to the second chamber, the second airflow having at least one of different temperature and pressure than the first airflow. 11. The method of claim 10 wherein: the first and second airflows are introduced through different spanwise ends of the spar. 12. The method of claim 10 wherein: the first airflow has a lower pressure than the second airflow. 13. A vane comprising: an airfoil shell having: a leading edge; a trailing edge; a pressure side; and a suction side; a spar within the shell; an outboard shroud at an outboard end of the shell; and an inboard platform at an inboard end of the shell, wherein the spar comprises: multi-chamber means in the spar for limiting thermal mechanical stress on the shell. 14. The vane of claim 13 further comprising: a first air inlet port in the platform; and a second air inlet port in the shroud. 15. The vane of claim 13 wherein: the shell is a CMC; and the spar is metallic. 16. A method for engineering a vane having: an airfoil shell having: a leading edge; a trailing edge; a pressure side; and a suction side; a spar within the shell; an outboard shroud at an outboard end of the shell; and an inboard platform at an inboard end of the shell, the method comprising: configuring a plurality of chambers within the spar to provide airflow to cavities between the spar and shell so as to provide a desired internal pressure distribution within the shell. 17. The method of claim 16 being a reengineering, wherein an external sectional shape of the shell is preserved from a baseline. 18. The method of claim 16 being a reengineering from a baseline configuration to a reengineered configuration wherein: operational extreme magnitudes of positive axial stress, negative axial stress, positive interlaminar tensile stress, and negative interlaminar tensile stress are all reduced by at least 50% from the baseline configuration to the reengineered configuration. 19. The method of claim 16 being a reengineering from a baseline configuration to a reengineered configuration wherein: the shell is thinned at least at one location along a leading tenth of the shell from the baseline configuration to the reengineered configuration. 20. The method of claim 16 wherein: the shell is a ceramic matrix composite; and the spar is a single metallic spar.