Turbine inlet guide vane with scalloped platform and related method
A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability.
1. A nozzle segment, comprising:
an inner platform configured to be connected with a casing of a gas turbine engine;
an outer platform configured to be connected with the casing, the outer platform being disposed apart from the inner platform in a radial direction of the gas turbine engine; and
a plurality of blades disposed between the inner and outer platforms and connected thereto, each blade having a leading edge, a trailing edge, a suction side, and a pressure side, wherein one of an inside surface of the inner platform or an inside surface of the outer platform is scalloped outwardly along a radial direction extending from the leading edge of the blade past the trailing edge of the blade and into a portion of the inside surface of the inner or outer platform that is proximate the trailing edge of the blade to form a scalloped region, wherein the scalloped region extends from the pressure side of one of the plurality of blades to the suction side of an adjacent one of the plurality of blades in a uniform line having end points substantially equidistant from the rotation axis of the nozzle so as to increase a throat area of the nozzle segment;
wherein the blades extend through the scalloped region to the inner platform and the outer platform.
2. The nozzle segment according to claim 1 , wherein the increase in the throat area is an increase in a radial annulus area of the throat and a distance from blade to blade remains unchanged.
3. The nozzle segment according to claim 1 , wherein the nozzle segment is an inlet guide vane segment.
4. The nozzle segment according to claim 1 , wherein the increase in throat area is such that the nozzle segment is configured to handle a 3% increase in a gas mass flow rate through the nozzle segment as compared to the nozzle segment without the throat area increase.
5. The nozzle segment according to claim 1 , wherein the throat area is defined by a plane extending perpendicularly from the suction side of a blade to the trailing edge on the pressure side of an adjacent blade.
6. A method of increasing a gas mass flow rate through a nozzle segment, the method comprising:
providing a nozzle segment including an inner platform configured to be connected with a casing of a gas turbine engine, an outer platform configured to be connected with the casing disposed apart from the inner platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the inner and outer platforms and connected thereto, each blade having a leading edge, a trailing edge, a suction side, and a pressure side; and
removing material from a portion of one of an inside surface of the inner platform or from an inside surface of the outer platform outwardly along a radial direction extending from the leading edge of the blade the trailing edge of the blade and into a portion of the inside surface of the inner or outer platform that is proximate the trailing edge of the blade to form a scalloped region that extends from the pressure side of one of the plurality of blades to the suction side of an adjacent one of the plurality of blades in a uniform line having end points substantially equidistant from the rotation axis of the nozzle so as to increase a throat area of the nozzle segment;
wherein the blades extend through the scalloped region to the inner platform and the outer platform.
7. The method according the claim 6 , wherein the increase in the throat area is an increase in a radial annulus area of the throat and a distance from blade to blade remains unchanged.
8. The method according the claim 6 , wherein the nozzle segment is an inlet guide vane segment.
9. The method according the claim 6 , wherein the increase in throat area is such that the nozzle segment is configured to handle a 3% increase in a gas mass flow rate through the nozzle segment as compared to the nozzle segment without the throat area increase.
10. The method according the claim 6 , wherein the throat area is defined by a plane extending perpendicularly from the suction side of a blade to the trailing edge on the pressure side of an adjacent blade.