Detailed mass transfer distribution in a ribbed coolant passage with a 180° bend

Chen, Y.; Nikitopoulos, Dimitris E.; Hibbs, Richard G.; Acharya, Sumanta; Myrum, T. A.

doi:10.1016/s0017-9310(99)00118-0

Cited by 27 publications

(11 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For the measurements, a rotating facility is already available in the Pi's laboratory (Fig. 1), and this facility has been used by the co-PIs to study heat transfer in the coolant channels with rotation {Hibbs Eliades et al, 1999) and without rotation (Hibbs et al, 1998;Hibbs et al, 1999). Velocity and temperature measurements, and RANS computations in the stationary frame have also been reported by the PI (Acharya et al 1994.…”

Section: Goalsmentioning

confidence: 99%

“…Till this point, all measurements made in this facility have been mass-transfer (naphthalene-sublimation) measurements (Hibbs et al, , 1997(Hibbs et al, , 1998(Hibbs et al, , 1999Chen et al, 1999;Eliades et al, 1999), which as pointed out earlier, do not incorporate centrifugal buoyancy effects. This facility will be modified for the present research to accommodate velocity measurements on the rotating frame, and liquid-crystal measurements with cryogenically cooled air also on the rotating frame.…”

Section: Figure 2 Rotating Channel Facilitymentioning

confidence: 99%

“…For the smooth stationary channel, secondary flows generated by Reynolds-stress anisotropies were also noted to be important (Chen et al, 1999).…”

Section: Figure 2 Rotating Channel Facilitymentioning

confidence: 99%

See 2 more Smart Citations

A 3D-PIV System for Gas Turbine Applications

Acharya¹

2002

View full text Add to dashboard Cite

Public reporting burden for this collection of information is estimated to average 1 hour per response gathering and maintaining the data needed, and completing and reviewing the collection of information, collection of information, including suggestions for reducing this burden, to Washington Headquarters S Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and>?jiiget.

show abstract

Section: Goalsmentioning

confidence: 99%

Section: Figure 2 Rotating Channel Facilitymentioning

confidence: 99%

See 1 more Smart Citation

A 3D-PIV System for Gas Turbine Applications

Acharya¹

2002

View full text Add to dashboard Cite

show abstract

“…The film cooling and the internal convection cooling have been studied extensively since 1960s and many papers can be found on their individual effects. For example, there are reports on the effects of the density ratio (1) , the blowing angle (2) , and the geometry of injection holes (3) (4) for the film cooling while there are reports on the effects of geometry of turbulence promoters (5) (6) , the passage bend (7) , and the blade rotation (8) for the internal convection cooling. In contrast, studies on the combined effects of the film cooling and the internal convection cooling are rather scarce except for a few studies such as those of Gritsch et al (9) , Fawcett et al (10) Kissel et al (11) , and Sakai et al (12) .…”

Section: Introductionmentioning

confidence: 99%

Effects of Turbulence Promoters of Gas Turbine Blades on Film Cooling Performance

Agata

Takahashi

Shimizu

et al. 2012

JTST

View full text Add to dashboard Cite

The effects of orientation of turbulence promoting ribs in the internal cooling air passage on the film cooling performance of outer surface of gas turbine blades have been studied experimentally. Both the adiabatic film cooling effectiveness and the heat transfer coefficient downstream of the film-cooling hole of a flat plate were measured for two different orientations of the turbulence promoting ribs. It is found that the adiabatic film cooling effectiveness and heat transfer coefficient on the external surface are considerably affected by the inversion of the rib orientation in the internal passage. The film cooling performance is evaluated in terms of the net heat flux reduction and the net surface temperature reduction, both of which are calculated from the measurement of adiabatic film cooling effectiveness and heat transfer coefficient. The evaluation of these quantities has clarified the effects of the internal cooling structure on the film cooling performance.

show abstract

“…Examples of such studies are Rau et al [7], Schabacker et al [8], Shih et al [9], and Chen et al [ 10]. Other studies, fewer in number, have sought to provide detailed heat transfer coefficient distrib utions within mUlti-pass serpentine turbulated cooling ci rcuits.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade: Part 1 — Experimental Measurements

Bunker

Wetzel

Rigby

2002

Volume 3: Turbo Expo 2002, Parts a and B

View full text Add to dashboard Cite

A combined experimental and computational study has been performed to investigate the detailed heat transfer coefficient distributions with in a complex blade trailing edge passage. The experimental measurements are made using a steady liquid crystal thermography technique applied to one major side of the passage. The geometry of the trailing edge passage is that of a two-pass serpentine circuit with a sharp ISO-degree turning region at the tip. The upflow channel is split by interrupted ribs into two major subchannels, one of which is turbulated. This channel has an average aspect ratio of rough ly 14: I. The spanwi e extent of the channel geometry includes both area convergence from root to tip, as well as taper towards the trailing edge apex. The average section Reynolds numbers tested in this upflow channel range from 55,000 to 9S,000. The tip section contains a turning vane near the extreme corner. The down flow channel has an aspect ratio of about 5: I, and also includes convergence and taper. Turbulators of vary ing sizes are included in thi channel also.Both detailed heat transfer and pressure distribution measurements are presented. The pre sure measurements are incorporated into a flow network model illustrating the major loss contributors.

show abstract

Detailed mass transfer distribution in a ribbed coolant passage with a 180° bend

Cited by 27 publications

References 12 publications

A 3D-PIV System for Gas Turbine Applications

A 3D-PIV System for Gas Turbine Applications

Effects of Turbulence Promoters of Gas Turbine Blades on Film Cooling Performance

Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade: Part 1 — Experimental Measurements

Contact Info

Product

Resources

About