Partially turbulated trailing edge cooling passages for gas turbine nozzles

Patent · Mon Jan 01 00:00:00 EST 2001

OSTI ID:873559

Thatcher, Jonathan Carl ^[1]; Burdgick, Steven Sebastian ^[1]

---

1. Schenectady, NY

A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing cooling air from the cavity through the passages through the tip of the trailing edge into the hot gas path. Each passage is partially turbulated and includes ribs in an aft portion thereof to provide enhanced cooling effects adjacent the tip of the trailing edge. The major portions of the passages are smooth bore. By this arrangement, reduced temperature gradients across the trailing edge metal are provided. Additionally, the inlets to each of the passages have a restriction whereby a reduced magnitude of compressor bleed discharge air is utilized for trailing edge cooling purposes.

• Research Organization: General Electric Co., Schenectady, NY (United States)
• DOE Contract Number: FC21-95MC31176
• Assignee: General Electric Co. (Schenectady, NY)
• Patent Number(s): US 6190120
• OSTI ID: 873559
• Country of Publication: United States
• Language: English

Related Subjects

partially
turbulated
trailing
edge
cooling
passages
gas
turbine
nozzles
plurality
spaced
length
nozzle
vane
lie
communication
cavity
flowing
air
tip
hot
path
passage
ribs
portion
provide
enhanced
effects
adjacent
major
portions
smooth
bore
arrangement
reduced
temperature
gradients
metal
provided
additionally
inlets
restriction
whereby
magnitude
compressor
bleed
discharge
utilized
purposes
nozzle vane
cooling passages
turbine nozzle
cooling air
temperature gradient
gas turbine
hot gas
major portion
trailing edge
reduced temperature
temperature gradients
provide enhanced
gas path
enhanced cooling
cooling purposes
discharge air
charge air
/415/416/