Bleed flow assembly for a gas turbine engine

A gas turbine engine comprising:

• a turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order, the turbomachine defining a core flow therethrough during operation;
• a first heat exchange assembly in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine through a first bleed flow path;
• a first heat exchange assembly valve located upstream of the first heat exchange assembly for control of the first bleed flow to the first heat exchange assembly;
• a bleed entry valve upstream of the first heat exchange assembly valve and configured to control the first bleed flow to the first heat exchange assembly valve;
• a first tap valve upstream of the bleed entry valve and configured to control the first bleed flow from the turbomachine;
• a secondary tap valve upstream of the of the bleed entry valve and configured to control a flow between a secondary pressure source and the bleed entry valve;
• a first flow outlet in fluid communication with the first heat exchange assembly for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly;
• a second heat exchange assembly in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine through a second bleed flow path;
• and
• a second flow outlet in fluid communication with the second heat exchange assembly for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly;
• wherein the first flow outlet is not in communication with the second aircraft flow assembly and wherein the second flow outlet is not in communication with the first aircraft flow assembly;
• wherein the first bleed flow path and the second bleed flow path operate independently of one another.