Abstract: A rotor blade 40 for a gas turbine engine has an aerofoil portion 42 from a root 48 to a tip 54. In use, combustion gas may leak over the tip 54 from the pressure face 52 to the suction face 50. A gutter 62 extends across the tip 54 to entrain any over tip leakage gap. The floor of the gutter defines an increased depth portion 72 at the exit end of the gutter 62.

Abstract: A turbine blade for a gas turbine engine has an aerofoil portion extending from a root to a tip. The tip carries winglets. A gutter extends across the tip to entrain gas leaking around the tip (over tip leakage). The aerofoil portion has a mean camber line and the gutter has a center line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the center line are parallel at the exit when viewed as aforesaid, are not both fulfilled.

Abstract: A rotor blade has a radially extending aerofoil body having pressure and suction sides. The rotor blade further has squealer tip. The squealer tip includes a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface which has a first outer surface. The peripheral wall further has, along at least part of at least one of the pressure and suction sides, at least one second region inclined outwardly of the cavity with respect to the radial direction of the blade which has a second outer surface which extends obliquely outwardly of the blade. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.

Abstract: A blade for a rotor, such as a turbine rotor of a gas turbine engine, has a squealer tip comprising a peripheral wall which defines a cavity. A first region of the peripheral wall extends radially, with its outer surface forming a continuation of the adjacent aerofoil surface of the blade. A second region extends obliquely with respect to the radial direction and the adjacent part of the aerofoil surface. The second region defines a winglet, and serves to increase the width of the chamber towards the trailing edge of the blade.

Abstract: A rotor blade has a radially extending aerofoil body having pressure and suction sides. The rotor blade further has squealer tip. The squealer tip includes a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface which has a first outer surface. The peripheral wall further has, along at least part of at least one of the pressure and suction sides, at least one second region inclined outwardly of the cavity with respect to the radial direction of the blade which has a second outer surface which extends obliquely outwardly of the blade. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.

Abstract: A rotor blade for a gas turbine engine has an aerofoil portion and a tip region. The tip region is at the radially outermost end of the blade. The radially outermost surface carries abrasive material (not shown) to interact with an abradable surface. The tip has a recess in which cooling air outlets are formed. The recess is open in a circumferential direction. This allows cooling air outlets to be formed without interference from the abrasive material, and inhibits any tendency for abrasion debris to collect in the recess and interfere with the flow of cooling air.

Abstract: A rotor blade 40 for a gas turbine engine has an aerofoil portion 42 from a root 48 to a tip 54. In use, combustion gas may leak over the tip 54 from the pressure face 52 to the suction face 50. A gutter 62 extends across the tip 54 to entrain any over tip leakage gap. The floor of the gutter defines an increased depth portion 72 at the exit end of the gutter 62.

Abstract: A turbine blade (40) for a gas turbine engine has an aerofoil portion (42) extending from a root (48) to a tip (54). The tip (54) carries winglets (56, 58). A gutter (62) extends across the tip (54) to entrain gas leaking around the tip (54) (over tip leakage). The aerofoil portion (42) has a mean camber line and the gutter (62) has a centre line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the centre line are parallel at the exit when viewed as aforesaid, are not both fulfilled.

Abstract: A blade for a rotor, such as a turbine rotor of a gas turbine engine, has a squealer tip comprising a peripheral wall which defines a cavity. A first region of the peripheral wall extends radially, with its outer surface forming a continuation of the adjacent aerofoil surface of the blade. A second region extends obliquely with respect to the radial direction and the adjacent part of the aerofoil surface. The second region defines a winglet, and serves to increase the width of the chamber towards the trailing edge of the blade.