Alternative W-seal groove arrangement

A blade outer air seal (BOAS) assembly, comprising:

• a rotor blade configured to rotate about an axis;
• a BOAS positioned radially outward from the rotor blade and having a BOAS main body, a BOAS aft radial portion extending radially outward from the BOAS main body, a BOAS aft axial portion extending axially aft from the BOAS aft radial portion, an aft wing extending aft from the BOAS main body, and an aft-facing BOAS face defined by the BOAS aft radial portion;
• a shroud block positioned radially outward from the BOAS, having a shroud main body, a shroud aft radial portion extending radially inward from the shroud main body, a shroud aft axial portion extending axially forward from the shroud aft radial portion, and a forward-facing shroud face defined by the shroud aft radial portion, the shroud block being configured to support the BOAS;
• and
• a bellows seal extending from the aft-facing BOAS face to the forward-facing shroud face and configured to reduce fluid leakage radially between the BOAS and the shroud block,
• wherein:
• the first bellows seal is located in a cavity having an aft edge defined by the shroud aft radial portion, a radially inner edge defined by the BOAS aft axial portion, a forward edge defined by the BOAS aft radial portion, and a radially outer edge defined by the shroud main body;
• and
• the shroud aft axial portion is located between the BOAS aft axial portion and the aft wing.

A gas turbine engine having an axis and comprising:

• a compressor section configured to compress a fluid;
• a combustor section configured to mix the fluid with fuel and combust the fluid and the fuel to generate exhaust;
• and
• a turbine section configured to receive the exhaust and convert the exhaust into torque,
• wherein at least one of the compressor section or the turbine section includes:
• a rotor blade configured to rotate about the axis,
• a BOAS positioned radially outward from the rotor blade and having a BOAS main body, a BOAS forward radial portion extending radially outward from the BOAS main body, a BOAS forward axial portion extending axially forward from the BOAS forward radial portion, a forward wing extending forward from the BOAS main body, and a forward-facing BOAS face defined by the BOAS forward radial portion,
• a shroud block positioned radially outward from the BOAS, having a shroud main body, a shroud forward radial portion extending radially inward from the shroud main body, a shroud forward axial portion extending axially aft from the shroud forward radial portion, and an aft-facing shroud face defined by the shroud forward radial portion, the shroud block being configured to support the BOAS, and
• a first bellows seal extending from the forward-facing BOAS face to the aft-facing shroud face and configured to reduce fluid leakage radially between the BOAS and the shroud block,
• wherein:
• the first bellows seal is located in a cavity having a forward edge defined by the shroud forward radial portion, a radially inner edge defined by the BOAS forward axial portion, an aft edge defined by the BOAS forward radial portion, and a radially outer edge defined by the shroud main body;
• and
• the shroud forward axial portion is located between the BOAS forward axial portion and the forward wing.