Flow guides for internal cooling of a cmc airfoil

A gas turbine engine including:

• a fan, a compressor section, a combustor and a turbine section;
• a ceramic matrix component (“CMC”) received within one of said combustor section and said turbine section,
• the CMC component having a radially outer end and a radially inner end, said ceramic matrix component having an internal cavity defined by an inner surface;
• a spar received within the internal cavity, and spaced from an inner surface of the CMC component defining a chamber with the inner surface;
• flow guides formed on one of an outer surface of said spar and said inner surface of said CMC component, said flow guides directing airflow towards a portion of the inner surface;
• an air inlet chamber being formed at one radial end of said spar and an air outlet chamber formed at an opposed radial end of said spar, and said air inlet chamber being defined such that air will flow into the internal chamber, outwardly of the spar, and inwardly of the inner surface of the CMC component;
• and
• at least a portion of the flow guides on the one of the outer surface and the inner surface contact the other of the outer surface and the inner surface.

A gas turbine engine including:

• a fan, a compressor section, a combustor and a turbine section;
• a ceramic matrix component (“CMC”) received within one of said combustor section and said turbine section,
• the CMC component having a radially outer end and a radially inner end, said ceramic matrix component having an internal cavity defined by an inner surface;
• a spar received within the internal cavity, and spaced from an inner surface of the CMC component defining a chamber with the inner surface;
• flow guides formed on one of an outer surface of said spar and said inner surface of said CMC component, said flow guides directing airflow towards a portion of the inner surface;
• an air inlet chamber being formed at one radial end of said spar and an air outlet chamber formed at an opposed radial end of said spar, and said air inlet chamber being defined such that air will flow into the internal chamber, outwardly of the spar, and inwardly of the inner surface of the CMC component;
• and
• wherein a source of air is communicated into the air inlet chamber directly without passing through the spar.