An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.

An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.

A steam turbine includes a guide member that is disposed between a first rotor blade row and a second stator vane row to guide a fluid from the first rotor blade row toward the second stator vane row. When seen in a circumferential direction, an outer peripheral surface of an inner ring of the second stator vane row is disposed farther to an inner side in a radial direction than an outer peripheral surface of a platform of the first rotor blade row. The guide member has a guide surface that extends from an outer peripheral surface of a shroud of the first rotor blade row toward an inner peripheral surface of an outer ring of the second stator vane row so as to be inclined toward the inner side in the radial direction as the guide surface approaches a second side from a first side in an axial direction.

A guide vane arrangement of a gas turbine and a method of manufacturing a guide vane arrangement of a gas turbine are provided herein. The guide vane arrangement includes a first guide vane device including a first radially inner platform and a first number of first airfoils, and a second guide vane device including a second radially inner platform and a second number of second airfoils. The first guide vane device and the second guide vane device are arranged along a circumferential direction of the turbine, wherein the first number of the first airfoils differs to the second number of the second airfoils. The first guide vane device is designed with a higher heat resistance than the second guide vane device.

A guide vane arrangement of a gas turbine and a method of manufacturing a guide vane arrangement of a gas turbine are provided herein. The guide vane arrangement includes a first guide vane device including a first radially inner platform and a first number of first airfoils, and a second guide vane device including a second radially inner platform and a second number of second airfoils. The first guide vane device and the second guide vane device are arranged along a circumferential direction of the turbine, wherein the first number of the first airfoils differs to the second number of the second airfoils. The first guide vane device is designed with a higher heat resistance than the second guide vane device.

An apparatus for extending the operational flow rate range of a turbine is described herein. Two or more removable sleeves may be used to change the cross-sectional area of a turbine. Each removable sleeve may define or eliminate the stator gap between a stator blade tip and an inner wall of the removable sleeve and a rotor gap between a rotor blade tip and an inner wall of the removable sleeve. A movable sleeve may be disposed in the turbine and may move between a first position and a second position in response to changes in the pressure differential across the turbine. The movable sleeve may define or eliminate a stator gap between a stator blade tip and the inner conical surface of the sleeve or a hub of the turbine and a rotor gap between a rotor blade tip and the inner conical surface of the sleeve.

An apparatus for extending the operational flow rate range of a turbine is described herein. Two or more removable sleeves may be used to change the cross-sectional area of a turbine. Each removable sleeve may define or eliminate the stator gap between a stator blade tip and an inner wall of the removable sleeve and a rotor gap between a rotor blade tip and an inner wall of the removable sleeve. A movable sleeve may be disposed in the turbine and may move between a first position and a second position in response to changes in the pressure differential across the turbine. The movable sleeve may define or eliminate a stator gap between a stator blade tip and the inner conical surface of the sleeve or a hub of the turbine and a rotor gap between a rotor blade tip and the inner conical surface of the sleeve.

A turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a tip distal from the outer wall segment such that the tips form a seal with the inner wall segments at an inner flow path of the turbine. An inner wall assembly and a turbine assembly method are also disclosed.

A turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a tip distal from the outer wall segment such that the tips form a seal with the inner wall segments at an inner flow path of the turbine. An inner wall assembly and a turbine assembly method are also disclosed.

A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 2, 3, and 4.