Turbine blade tip flow discouragers
- Niskayuna, NY
A turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationery shroud. The rotating blade portions comprise a root section, a tip portion and an airfoil. The tip portion has a pressure side wall and a suction side wall. A number of flow discouragers are disposed on the blade tip portion. In one embodiment, the flow discouragers extend circumferentially from the pressure side wall to the suction side wall so as to be aligned generally parallel to the direction of rotation. In an alternative embodiment, the flow discouragers extend circumferentially from the pressure side wall to the suction side wall so as to be aligned at an angle in the range between about 0.degree. to about 60.degree. with respect to a reference axis aligned generally parallel to the direction of rotation. The flow discouragers increase the flow resistance and thus reduce the flow of hot gas flow leakage for a given pressure differential across the blade tip portion so as to improve overall turbine efficiency.
- Research Organization:
- General Electric Co., Schenectady, NY (United States)
- DOE Contract Number:
- FC21-95MC31176
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Number(s):
- US 6027306
- OSTI ID:
- 872862
- Country of Publication:
- United States
- Language:
- English
A Summary of the Cooled Turbine Blade Tip Heat Transfer and Film Effectiveness Investigations Performed by Dr. D. E. Metzger
|
conference | February 2015 |
Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel
|
journal | February 1989 |
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Related Subjects
blade
tip
flow
discouragers
assembly
comprises
plurality
rotating
portions
spaced
relation
stationery
shroud
comprise
root
section
portion
airfoil
pressure
wall
suction
disposed
embodiment
extend
circumferentially
aligned
parallel
direction
rotation
alternative
angle
range
degree
60
respect
reference
axis
increase
resistance
reduce
hot
gas
leakage
differential
improve
overall
efficiency
rotating blade
turbine assembly
reference axis
spaced relation
assembly comprises
tip portion
turbine blade
gas flow
pressure differential
hot gas
alternative embodiment
blade tip
turbine efficiency
blade portions
extend circumferentially
root section
flow resistance
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