Turbine blade tip flow discouragers
Patent
·
OSTI ID:872862
- 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 Company (Schenectady, NY)
- 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
/415/416/
60
airfoil
aligned
alternative
alternative embodiment
angle
assembly
assembly comprises
axis
blade
blade portions
blade tip
circumferentially
comprise
comprises
degree
differential
direction
discouragers
disposed
efficiency
embodiment
extend
extend circumferentially
flow
flow resistance
gas
gas flow
hot
hot gas
improve
increase
leakage
overall
parallel
plurality
portion
portions
pressure
pressure differential
range
reduce
reference
reference axis
relation
resistance
respect
root
root section
rotating
rotating blade
rotation
section
shroud
spaced
spaced relation
stationery
suction
tip
tip portion
turbine
turbine assembly
turbine blade
turbine efficiency
wall
60
airfoil
aligned
alternative
alternative embodiment
angle
assembly
assembly comprises
axis
blade
blade portions
blade tip
circumferentially
comprise
comprises
degree
differential
direction
discouragers
disposed
efficiency
embodiment
extend
extend circumferentially
flow
flow resistance
gas
gas flow
hot
hot gas
improve
increase
leakage
overall
parallel
plurality
portion
portions
pressure
pressure differential
range
reduce
reference
reference axis
relation
resistance
respect
root
root section
rotating
rotating blade
rotation
section
shroud
spaced
spaced relation
stationery
suction
tip
tip portion
turbine
turbine assembly
turbine blade
turbine efficiency
wall