Variable stator vane arrangement

The gas turbine engine according to claim 14, wherein:

• the turbine is a first turbine, the compressor is a first compressor, and the core shaft is a first core shaft;
• the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor;
• and
• the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.
• The gas turbine engine according to claim 15, wherein the second compressor comprises,
• a radially inner flow boundary;
• a radially outer flow boundary;
• an annular array of variable stator vanes, each stator vane extending from a first end at the radially inner flow boundary to a second end at the radially outer flow boundary, wherein:
• at least one of the radially inner flow boundary and the radially outer flow boundary is faceted, such that the surface of the faceted flow boundary comprises flat portions at the interfaces with the respective first or second end of each stator vane.