Gas turbine engine compressor arrangement

An arrangement for a gas turbine engine comprising:

• a fan section having a central axis;
• a compressor case for housing a compressor;
• an inlet case for guiding air to the compressor, the compressor case positioned axially further from the fan section than the inlet case;
• a support member extending between the fan section and the compressor case wherein the support member restricts movement of the compressor case relative to the inlet case;
• the compressor case includes an upstream compressor case portion and a downstream compressor case portion, the downstream compressor case portion being axially further from the inlet case than the upstream compressor case portion, wherein the support member extends between the fan section and the upstream compressor case portion, and the inlet case is removable from the gas turbofan engine separately from the compressor case;
• the compressor case includes a low pressure compressor section and a high pressure compressor section.

A gas turbine engine comprising:

• a fan section;
• a compressor section, including both a low pressure compressor section and a high pressure compressor section;
• and
• an overall pressure ratio being above or equal to about 35 and being provided by the combination of the low pressure compressor section and the high pressure compressor section, with the overall pressure ratio being provided by a pressure ratio across the low pressure compressor section, and a pressure ratio across the high pressure compressor section, and the pressure ratio across one of the low pressure and high pressure compressor sections being between about 7 and about 15 to provide the overall pressure ratio,
• wherein the fan delivers a portion of air into the compressor section and a portion of air into a bypass duct, and
• wherein a pressure ratio across the fan section being less than or equal to about 1.45.