Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A locking arrangement for a row of radial entry blades (62) of a turbo-machine. A closing blade (66) includes a root portion (74) having an axial attachment shape (78) for engagement with an axially oriented slot having an axial attachment shape (76) formed at the entering slot location (34) of the radial entry rotor disk (56). For applications utilizing blades with curved platform faces (112), a preceding blade (108) and a following blade (110) in the row are designed with one curved face for abutting adjacent radial entry blades and one flat face (120) for abutting the flat closing blade faces (116). The closing blade (84) may be designed with a root portion (88) having two legs (90,92) that are urged apart by a key (86) into tight contact with the adjacent blades.

Abstract: A locking arrangement for a row of radial entry blades (62) of a turbo-machine. A closing blade (66) includes a root portion (74) having an axial attachment shape (78) for engagement with an axially oriented slot having an axial attachment shape (76) formed at the entering slot location (34) of the radial entry rotor disk (56). For applications utilizing blades with curved platform faces (112), a preceding blade (108) and a following blade (110) in the row are designed with one curved face for abutting adjacent radial entry blades and one flat face (120) for abutting the flat closing blade faces (116). The closing blade (84) may be designed with a root portion (88) having two legs (90,92) that are urged apart by a key (86) into tight contact with the adjacent blades.