Diffusers, gas turbine engines comprising the same, and methods for operation thereof

A gas turbine engine, comprising:

• a compressor section including:
• an impeller configured to pressurize an intake fluid to produce a compressed fluid;
• and
• a diffuser configured to receive the compressed fluid in passages thereof, wherein the passages are partitioned by diffuser vanes each including a first vane sidewall, a second vane sidewall opposite the first vane sidewall, a hub-side endwall, and a shroud-side endwall opposite the hub-side endwall, wherein each of the diffuser vanes have a thickness between the first vane sidewall and the second vane sidewall and a tapered cross-sectional profile portion, wherein the thickness of each of the diffuser vanes within the tapered cross-sectional profile portion decreases from the shroud-side endwall to the hub-side endwall;
• a combustion section configured to form a mixture of the compressed fluid with a fuel and combust the mixture to form an exhaust;
• and
• a turbine section configured to rotate in response to receiving the exhaust.

A method of operating an engine, comprising:

• receiving a compressed fluid from an impeller into passages of a diffuser;
• modifying a flow of the compressed fluid with diffuser vanes partitioning the passages, wherein the diffuser vanes each include a first vane sidewall, a second vane sidewall opposite the first vane sidewall, a hub-side endwall, and a shroud-side endwall opposite the hub-side endwall, wherein each of the diffuser vanes having a thickness between the first vane sidewall and the second vane sidewall and a tapered cross-sectional profile portion, wherein the thickness of each of the diffuser vanes within the tapered cross-sectional profile portion decreases from the shroud-side endwall to the hub-side endwall;
• and
• directing the compressed fluid from the diffuser to a combustor.