Abstract:Blade tip aerodynamic loss results from experimental and numerical investigations are presented for engine representative conditions downstream of a blade row with an exit Mach number Mexit of 1.0, and an exit Reynolds number Reexit of 1.27×106 (based on axial chord). These results are presented for three different tip gaps of 0.5, 1.0, and 1.5 percent relative to engine-equivalent blade span. Experimental data are obtained by traversing a specially-made and calibrated three-hole pressure probe as well as a si… Show more
“…Most recently, the over tip choking and shock structure were reported for a shroudless flat tip (Zhang et al [26]), and even a modern winglet tip design (O'Dowd et al [27]). Similar results have also been reported by Shyam et al [28,29] in their numerical study for a highly The present computational analysis using an extensively developed CFD code which has been recently validated for transonic blade tip configurations [25], [26], [31] should shed some light on this primary issue. Furthermore, one may ask, are there any advantageous implications if a leakage flow is made choked?…”
Section: B Problem Statement and Motivation Of The Present Worksupporting
confidence: 72%
“…Some preliminary evaluations of the influence of a moving casing have been reported by Zhang et al [26], O'Dowd et al [31] for the same and similar transonic blade tip configurations. Their results suggest that while a moving wall can reduce the size of the transonic region, a significant part of tip (over 40 percent) still remains transonic.…”
Section: High-load Blading Design With Relatively Low Tip Leakagementioning
“…Most recently, the over tip choking and shock structure were reported for a shroudless flat tip (Zhang et al [26]), and even a modern winglet tip design (O'Dowd et al [27]). Similar results have also been reported by Shyam et al [28,29] in their numerical study for a highly The present computational analysis using an extensively developed CFD code which has been recently validated for transonic blade tip configurations [25], [26], [31] should shed some light on this primary issue. Furthermore, one may ask, are there any advantageous implications if a leakage flow is made choked?…”
Section: B Problem Statement and Motivation Of The Present Worksupporting
confidence: 72%
“…Some preliminary evaluations of the influence of a moving casing have been reported by Zhang et al [26], O'Dowd et al [31] for the same and similar transonic blade tip configurations. Their results suggest that while a moving wall can reduce the size of the transonic region, a significant part of tip (over 40 percent) still remains transonic.…”
Section: High-load Blading Design With Relatively Low Tip Leakagementioning
“…The stagnation pressure, stagnation temperature and flow angle are specified at inlet, and the static pressure at exit. [31]. HYDRA numerical predictions give overall good agreement, as shown in Fig 2b. Generally, the sizes and magnitudes of the over tip leakage loss core are similar in both Fig.…”
Section: Computational Methods and Validationsupporting
“…The uncertainty associated with the aerodynamic loss has been conducted by O'Dowd et al [36]. Again, since the testing facility and apparatus used are identical, the estimated uncertainty is also valid here.…”
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.