Heat temperature gradient heat exchanger

A cooled cooling air system for a gas turbine engine comprising:

• a first source of airflow at a first pressure and temperature;
• a second source of airflow at a second pressure and temperature, the second temperature and pressure less than the first temperature and pressure;
• and
• a heat exchanger assembly including:
• an outer manifold defining an outer cavity and a cold inlet in communication with airflow from the second source;
• an inner shell defining an inner cavity, the inner shell supported within the outer manifold and at least partially surrounded by the outer cavity, the inner shell including a plurality of impingement openings for directing airflow from the outer manifold into the inner cavity;
• and
• an inner manifold supported within the inner cavity and a hot inlet in communication with airflow from the first source, wherein the inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell, the inner manifold including a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages.

A gas turbine engine assembly comprising:

• a compressor section including a bleed air opening for a first source of airflow at a first pressure and first temperature;
• a second source of airflow at a second pressure and a second temperature;
• a heat exchanger assembly including;
• an outer manifold defining an outer cavity and a cold inlet in communication with airflow from the second source,
• an inner shell defining an inner cavity, the inner shell supported within the outer manifold and at least partially surrounded by the outer cavity, the inner shell including a plurality of impingement openings for directing airflow from the outer manifold into the inner cavity;
• and
• an inner manifold supported within the inner cavity and a hot inlet in communication with airflow from the first source, wherein the inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell, the inner manifold including a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages;
• and
• a turbine section including at least one cooling air passage receiving cooled airflow from an outlet of the inner manifold.