Prashant B. Godse, Harshal D. Akolekar, A. M. Pradeep
{"title":"在近失速条件下运行的跨音速轴流压缩机中的表面粗糙度效应","authors":"Prashant B. Godse, Harshal D. Akolekar, A. M. Pradeep","doi":"arxiv-2409.07344","DOIUrl":null,"url":null,"abstract":"Surface roughness is a major contributor to performance degradation in gas\nturbine engines. The fan and the compressor, as the first components in the\nengine's air path, are especially vulnerable to the effects of surface\nroughness. Debris ingestion, accumulation of grime, dust, or insect remnants,\ntypically at low atmospheric conditions, over several cycles of operation are\nsome major causes of surface roughness over the blade surfaces. The flow in\ncompressor rotors is inherently highly complex. From the perspective of the\ncomponent designers, it is thus important to study the effect of surface\nroughness on the performance and flow physics, especially at near-stall\nconditions. In this study, we examine the effect of surface roughness on flow\nphysics such as shock-boundary layer interactions, tip and hub flow\nseparations, the formation and changes in the critical points, and tip leakage\nvortices amongst other phenomena. Steady and unsteady Reynolds Averaged Navier\nStokes (RANS) calculations are conducted at near-stall conditions for smooth\nand rough NASA (National Aeronautics and Space Administration) rotor 67 blades.\nSurface streamlines, Q-criterion, and entropy contours aid in analyzing the\nflow physics qualitatively and quantitatively. It is observed that from the\nonset of stall, to fully stalled conditions, the blockage varies from 21.7\\% to\n59.6\\% from 90\\% span to the tip in the smooth case, and from 40.5\\% to 75.2\\%\nin the rough case. This significant blockage, caused by vortex breakdown and\nchaotic flow structures, leads to the onset of full rotor stall.","PeriodicalId":501125,"journal":{"name":"arXiv - PHYS - Fluid Dynamics","volume":"12 1","pages":""},"PeriodicalIF":0.0000,"publicationDate":"2024-09-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Surface roughness effects in a transonic axial flow compressor operating at near-stall conditions\",\"authors\":\"Prashant B. Godse, Harshal D. Akolekar, A. M. Pradeep\",\"doi\":\"arxiv-2409.07344\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"Surface roughness is a major contributor to performance degradation in gas\\nturbine engines. The fan and the compressor, as the first components in the\\nengine's air path, are especially vulnerable to the effects of surface\\nroughness. Debris ingestion, accumulation of grime, dust, or insect remnants,\\ntypically at low atmospheric conditions, over several cycles of operation are\\nsome major causes of surface roughness over the blade surfaces. The flow in\\ncompressor rotors is inherently highly complex. From the perspective of the\\ncomponent designers, it is thus important to study the effect of surface\\nroughness on the performance and flow physics, especially at near-stall\\nconditions. In this study, we examine the effect of surface roughness on flow\\nphysics such as shock-boundary layer interactions, tip and hub flow\\nseparations, the formation and changes in the critical points, and tip leakage\\nvortices amongst other phenomena. Steady and unsteady Reynolds Averaged Navier\\nStokes (RANS) calculations are conducted at near-stall conditions for smooth\\nand rough NASA (National Aeronautics and Space Administration) rotor 67 blades.\\nSurface streamlines, Q-criterion, and entropy contours aid in analyzing the\\nflow physics qualitatively and quantitatively. It is observed that from the\\nonset of stall, to fully stalled conditions, the blockage varies from 21.7\\\\% to\\n59.6\\\\% from 90\\\\% span to the tip in the smooth case, and from 40.5\\\\% to 75.2\\\\%\\nin the rough case. This significant blockage, caused by vortex breakdown and\\nchaotic flow structures, leads to the onset of full rotor stall.\",\"PeriodicalId\":501125,\"journal\":{\"name\":\"arXiv - PHYS - Fluid Dynamics\",\"volume\":\"12 1\",\"pages\":\"\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2024-09-11\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"arXiv - PHYS - Fluid Dynamics\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/arxiv-2409.07344\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"arXiv - PHYS - Fluid Dynamics","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/arxiv-2409.07344","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Surface roughness effects in a transonic axial flow compressor operating at near-stall conditions
Surface roughness is a major contributor to performance degradation in gas
turbine engines. The fan and the compressor, as the first components in the
engine's air path, are especially vulnerable to the effects of surface
roughness. Debris ingestion, accumulation of grime, dust, or insect remnants,
typically at low atmospheric conditions, over several cycles of operation are
some major causes of surface roughness over the blade surfaces. The flow in
compressor rotors is inherently highly complex. From the perspective of the
component designers, it is thus important to study the effect of surface
roughness on the performance and flow physics, especially at near-stall
conditions. In this study, we examine the effect of surface roughness on flow
physics such as shock-boundary layer interactions, tip and hub flow
separations, the formation and changes in the critical points, and tip leakage
vortices amongst other phenomena. Steady and unsteady Reynolds Averaged Navier
Stokes (RANS) calculations are conducted at near-stall conditions for smooth
and rough NASA (National Aeronautics and Space Administration) rotor 67 blades.
Surface streamlines, Q-criterion, and entropy contours aid in analyzing the
flow physics qualitatively and quantitatively. It is observed that from the
onset of stall, to fully stalled conditions, the blockage varies from 21.7\% to
59.6\% from 90\% span to the tip in the smooth case, and from 40.5\% to 75.2\%
in the rough case. This significant blockage, caused by vortex breakdown and
chaotic flow structures, leads to the onset of full rotor stall.