T-AXI Blade V1.8 User Manual
Contents
1. Inlet To 394 44 K Inlet Po 267563 80 Pa y 1 38 AT 51 12 K n Rotor 0 91 Tie Pitch 0 2898 m Tte Pitch 0 2909 m w 12 300 rpm Dle 4 22 Degrees Pte 3 84 Degrees m 54 40 kg s Omle 15 80 Degrees Vm Ratio 0 91 A z Tip 0 027 m Number of Blades 50 Blade Thickness at Hub chord 10 85 Blade Thickness at Tip chord 2 61 16 4 3 1 2 9 10 Step By Step Procedure Start T Axi Blade by running the executable named TAXI BLADE V1 8 exe Click OK at the splash screen A file selection prompt should appear Navigate to the INPUTS folder and select EEE_3RD_STAGE tri This file contains all of the relevant input information shown in table 5 The Choose Interface Options screen should appear Check over the input values before proceeding The configuration type should be set to Large HPC HPT Press Refresh if the configuration is incorrect Click OK to proceed to the main program interface The main program interface displaying the Data Printout tabular output The input sliders on the left have all be set using the information in the input file Verify that these are correct Feel free to modify any of sliders to instantly see the effect on the blade shape and vector triangles Press Back to return to the previous to the previous screen and then reload the correct EEE 3rd Stage inputs Use the Display pull down selector to cycle through the different outputs2. View the velocity triangles at the Hub Pitch and Tip by selecting the appropriate display option The information shown graphically on these pages is also shown in a tabular form in the Data Printout window Select the Equations display option to view the equations used to solve for the blade row performance and velocity triangle quantities Press the Save Disk Output button to create a file for use in T Axi Disk Press the Quit button to close T Axi Blade The flow relative Mach number M and the relative flow angle 8 were compared to reference data at the hub pitch and tip Reference data is available at many more locations along the blade Figure 12 shows this comparison at the blade leading edge and Figure 13 shows this comparison at the trailing edge The data correlates very well at the mid span location but there is a significant amount of deviation at the hub and casing locations This discrepancy is due to the simplifications included in T Axi Blade The reference data was calculated using a proprietary axisymmetric code with empirical loss models T Axi Blade uses a free vortex assumption with constant spanwise efficiency Overall the two results correlate well but they clearly show the limitations of a low fidelity analysis tool 17 70 00 60 00 _ pde e 350 00 5 540 00 Ej amp 30 00 3 20 00 a Published Data 10 00 T Axi Bl
3. e Hub View Displays a radial view of the hub cross section of the blade row and all relevant data and vector triangles e Pitch View Same as Hub View with data displayed changing to reflect pitch values e Tip View Same as Hub View with data displayed changing to reflect tip values e Data Printout Text printout of input values and simulation output e Smith Chart Smith Chart showing values for the hub pitch and tip e Loading vs AR Loading vs Aspect Ratio chart e Equations Shows a formatted equations sheet solved for the current design Material Menu Drop down menu for blade material selection The menu consists of the material files of the dmat type stored in the MATERIALS folder Default options include several alloys such as INCONEL 706 INCONEL 718 and A286 to name a few Save Disk Output Saves the blade geometry dsk and flowpath dimensions for use in T AXI Disk to a din file 2 3 Program Output Modes Figure 3 shows the axial view output from the T AXI Blade main window An overview of the displayed data indicated with red numbers is given below Geometry Leading Edge Trailing Edge Vector Triangles Figure 3 T AXI Blade Axial View 1 Meridional Velocity Vm This is the magnitude of the meridional velocity vector shown in 6 2 Radial Velocity V This is the magnitude of the radial velocity vector shown in 6 3 Axial Velocity V This is the magnitude of the axial velocity vector sh
4. Program Interface 2 1 Program Initialization and Setup Upon execution of T Axi Blade the user is presented with a splash screen showing copyright and author information Clicking on the OK button brings the user to the blade file loading menu The user should select a blade input file tri from this prompt and then click Open to continue The default blade file is for a first stage axial compressor section and will load automatically if Cancel is pressed This should be used if a input file has not been created yet The Choose Interface Options window appears after the selection of a valid blade input file This windows reads and presents the information from the tri file chosen in the previous step Figure 1 shows this window The user should investigate the options carefully before continuing Any changes to these conditions should be made at this step Clicking the OK will take the user to the main T Axi Blade window L Choose Interface Options TBR Operators Configuration HLE Mdot Enabled Mdot Default Input Ulep RPM FT Input werspeed Fact Large HPCHPT Pressure Temp Load File Figure 1 T AXI Blade Interface Options Window 2 2 Main Program Window Figure 2 shows the main T Axi Blade window This window contains all of the controls needed to design and analyze a blade and blade row A short explanation of the controls marked with the red numbers is shown below L T AXI Bl
5. 2002 3 S J Cline W Fesler H S Liu R C Lovell and S J Shaffer Energy efficient engine high pres sure compressor component performance report Technical report General Electric Company Prepared for NASA 1985 Nasa Report Number CR 168245 4 D C Wisler C C Koch and L H Smith Preliminary design study of advanced multistage axial flow core compressors Technical report General Electric Company Prepared for NASA 1977 Nasa Report Number CR 135133 19
6. N Rotational Speed RPM P Pressure R Gas constant T Temperature U Rotor wheel speed V Absolute flow velocity W Rotor relative velocity GREEK a Absolute flow angle B Relative flow angle y Ratio of specific heats p Density c Stress w Rotor angular velocity SUBSCRIPTS a Annulus h Hub le Leading edge p Pitch t Tip te Trailing edge Z Axial T Total 0 Tangential direction 11 3 2 Establishing a Coordinate System and Vector Triangles Due to the lack of a standard coordinate system in the realm of turbomachinery one must clearly define the system before hoping to communicate clearly The system used by T AXI Blade is that used by GE Aviation as it was the most familiar system to the authors Figure 8 shows the coordinate system z engine axis w Figure 8 T AXIS Blade Coordinate System T AXI Blade is able to handle calculations for both axial and centrifugal configurations This is attained by following the meridional streamsurfaces shown in figure 9 The blade cross sections for hub pitch and tip are created by cutting along the m coordinate r r m m Figure 9 Axial and Centrifugal Streamsurfaces The vector triangle notation used in T AXI Blade is shown in figure 10 The triangle on the right shows the axisymmetric properties of the flow Vm is the meridional flow V is the axial component of the flow and V is the the radial component of the flow The triangle on the left 12 repr
7. T AXI Blade V1 8 User Manual Kevin Park amp David Gutzwiller 05 30 09 Contents 1 Introduction 1 1 License Information 246 A Re ER epe ed 1 2 Code Overview and Features llle 1 3 System Requirements 000 0 pe ee I Installation t dme aaa Le Xu RM REG Program Interface 2 1 Program Initialization and Setup ee 2 2 Main Program Window 202 nos oe ooo xe Rem mr RUE a a oe 2 3 Program Output Modes ls Background 34 Nomeuclat re s yon uius el UR Debs rk dd pc RR a VE RSS eie 3 2 Establishing a Coordinate System and Vector Triangles 3 8 T AXI Blade Theory of Operation 2 2 2 2 Cm mm nn Example Analysis EEE 3rd Stage Rotor AJA Background 4 2 2 By Pet eee OG SEE TE ae 4 2 Problem Setup 2 32 22 EE Ge Eee Gt SMe de Pak Se eR ROME eX Eo mg 4 8 Step By Step Procedure En nn nn Bug Reporting and Additional Help 11 11 12 14 15 15 16 17 20 1 Introduction 1 1 License Information T Axi Blade is released under the GNU General Public License Version 3 29 June 2007 Please see the included file gpl license txt for information regarding reproduction and distribu tion 1 2 Code Overview and Features T Axi Blade is a GUI based free vortex blade row design and visualization program The primary purpose of T Axi Blade is to develop students physical understanding of key blade design features with a special emphasis on the rel
8. Temperature at Trailing Edge Temperature Ratio 497 288 0K 492 193 0 Pressure Ratio PR 1 M TR 1 7 3 118 1 0 7800 1 492 1 Specific Heat Area of the Leading Edge 0 7981 03m lt 0 1710 01mx0 7428 02m Figure 6 T AXI Blade Equation Printout Equations Page 2 Specific Rotor Work Euler s O le 0 9543 055 Mass Flow Tn o V Ay 0 2110 E 1 Rotor Power T W m AH 0 2014 V theta at y y Leading Edge Yay Vm tan m 34 49 189 8 tan 0 1798 rV theta at H Trailing Edge WAO 2 O m _ 0 9543E 05 8 876 5 1008E 03 Figure 7 T AXI Blade Equation Printout 10 3 Background 3 1 Nomenclature T AXI was created using the nomenclature shown below There are however many nomenclature systems in use throughout academia and the industry with none being especially better than the other The key is to establish a system and then be consistent The chosen nomenclature system and one alternative is shown in table 1 Table 1 TURBOMACHINERY NOMENCLATURE Property T Axi Blade Alternatives Engine Axis x Absolute velocity V C Relative velocity W V Tangential velocity Vo Cu Angular momentum rVo go Table 2 General Nomenclature NOMENCLATURE a Speed of sound r Radius or radial station A Area M Mach number
9. ade Results 0 00 T T T T 0 23 0 25 0 27 0 29 0 31 0 33 0 35 Radius m 12 5 E E O 308 E 30 6 204 Published Data 30 2 E T Ai Blade Results 0 T T T 0 23 0 25 0 27 0 29 0 31 0 33 0 35 Radius m Figure 12 BLADE RESULTS COMPARISON LEADING EDGE 70 60 gs0 2 540 230 320 Published Data s T Axi Blade Results 04 T T T T T 0 23 0 25 0 27 0 29 0 31 0 33 0 35 Radius m 0 800 50 700 e 2 E0 600 20 500 E 400 g 0 300 30 200 Published Data 20 100 T Axi Blade Results 0 000 r 0 23 0 25 0 27 0 29 0 31 0 33 0 35 Radius m Figure 13 BLADE RESULTS COMPARISON TRAILING EDGE 18 5 Bug Reporting and Additional Help Effort has been taken to develop T Axi Disk into a stable user friendly program However this software is new and most likely a number of bugs still exist Please contact the author with any bug reports using the information below Any questions or comments regarding the current state of T Axi Disk or ideas for its expansion are also welcome Michael Downing University of Cincinnati Department of Aerospace Engineering Email m_downing fuse net Office 436 ERC References 1 H L H Saravanamutto G F C Rogers and H Cohen Gas Turbine Theory 5th Edition Pearson Education New Jersey 2001 2 J Mattingly Aircraft Engine Design 2nd Ed AIAA Reston VA
10. ade V1 5 Exit Help l I Save Disc Output 1 V 7 188 23 Figure 2 T AXI Blade Main Window 1 Phi 9 Allows the user to change Phi angle between the engine axis and the meridional at the leading edge r and at the trailing edge dre 2 Vin Meridional velocity m s at the leading edge The ratio of velocities between the leading and trailing edges is adjusted with the slider to the right 3 R Pitch Radius from engine centerline to the pitch of the blade leading or trailing edge respectively 4 Mdot m Sets the mass flow rate across the stage in kilograms second 5 RPM Sets the design speed RPM 10 11 12 13 14 15 Eta rotor Nro Specifies rotor efficiency Delta TT ATr Specifies change in Total Temperature Kelvin across the rotor Alpha mle Pitch amie Specifies the angle deg between the velocity m s of the fluid entering the stage and its meridional component at the leading edge Delta Z Specifies the engine axis length of the blade Blade Thickness Sets the blade thickness at the hub meters with the slider to the right setting the thickness at the tip Blades Specifies the number of blades in the current row Save Inputs Saves the input conditions to a tri file View Selector Changes the view between different options Options are e Axial View Displays an axial view of the blade along with relevant data and vector triangles
11. ationship between velocity triangles and blade shapes The specific features of this code are summarized below e Support for axial and centrifugal compressor and turbine designs e GUI driven design and analysis e Detailed data output including vector triangles and values cascade views for hub pitch and tip Smith Charts and Loading vs Aspect Ratio charts e Formatted output of common turbomachinery equations solved for the current blade row design e Temperature dependant material database e Preliminary design stress analysis based on AN values 1 3 System Requirements Operating System Windows 2000 XP Vista Processor Pentium 3 or faster recommended Memory 256 MB or greater Display 1024 x 768 with 256 colors 1 4 Installation T Axi Blade and the related T Axi Disk codes are available from the University of Cincinnati GTSL website http GTSL ase uc edu T AXI Download the file BD SUITE zip and extract the entire package to a known location on your hard drive The unzip process should create all of the necessary files and folders Input files are contained in the subdirectory named INPUTS the material database is located under MATERIALS and documentation is located under HELP The user should be careful not to change the file structure of T Axi Disk as it may render the code inoperable Double clicking on the TAXI BLADE V1 8 exe icon will load the T Axi Blade GUI 2
12. ding edge is parallel to the relative velocity vector W and the camber line at the trailing edge is parallel to the exiting relative velocity W This is critical to reduce losses and maximize efficiency Once T AXI has found the blade shape it performs a basic structural analysis in the form of AN Comparison to theoretical maximum material dependant AN values then determines if the design is feasible The calculations eqs 25 amp 26 assume units of rad for omega and m x RPM for AN 2 AN Aww 25 AN 3600 osty m1 44 paf 4 Example Analysis EEE 3rd Stage Rotor 4 1 Background The GE Energy Efficient Engine EEE high pressure compressor HPC shown in Figure 11 below was designed in the late 1970s Eventually many features of this design were used in the GE90 turbofan Many of the documents and designs from this project are publicly available making the EEE a perfect test case for verifying results from a new program The third stage rotor and supporting disk have been chosen to demonstrate the capabilities of T Axi Blade and T Axi Disk 15 4 2 Problem Setup T Axi Blade was run first Table 5 shows the inputs that were used to build the T Axi Blade input file tri The majority of these values were taken or derived from the available EEE documents 3 4 Figure 11 EEE 10 STAGE COMPRESSOR CROSS SECTION Table 5 EEE 3RD STAGE ROTOR INPUTS
13. esents the flow as viewed in the cross sectional plane The reader may reference table 3 for the meaning of each term Figure 10 Vector Triangle Notation Table 3 Vector Triangle Nomenclature Term Definition V Absolute velocity of the flow W Relative velocity of the flow as seen by the blade row V Axial component of flow V Radial component of flow U Tangential velocity of blade row at a given radius hub pitch tip Om Angle between the meridional and absolute flow vectors Bm Angle between the meridional and relative flow vectors Angle between the axial and meridional flow vectors The governing equations which are used to produce the vector triangle magnitudes are shown as equations 1 12 These are standard turbomachinery equations stemming from the geometry of the system and the coordinate system chosen V W U 1 V Vk Vri Vaio 2 W Wk Wii Woig 3 W Vz W V 4 d xr uwri 5 Wo Vo U Vg wr 6 V ua dni x 7 13 Va V V 8 tana 9 W tan d v 10 V tan Om v 11 W tan Im z 12 3 3 T AXI Blade Theory of Operation T AXI Blade solves for blade geometry using straightforward turbomachinery calculations with the free vortex assumption Several good sources on for students to reference are the introductory texts by Saravanamutto 1 and Mattingly 2 The free vortex assumption requires a uniform a
14. ngular momentum distribution which leads to a clearly defined tangential velocity profile where r is the radius and Vg is the tangential velocity rV constant 13 Table 4 T AXI BLADE INPUTS ATT Rotor total temperature change Pr Inlet total pressure Tr Inlet total temperature CIGV Mrotor IGV loss coefficient and rotor efficiency Tle AZle Tte Blade geometry values Ule Vric VZte Known flow velocities Amie Meridional flow angle at leading edge R y Fluid properties N Rotational speed RPM Using the inputs shown in table 4 and assuming an ideal gas the following general equations hold a RT 14 V Ma 15 T T Ge P aan P f RT 18 Mass flow continuity is maintained across the rotor as shown in equations 20 and 21 m pVnA 20 Ale 27 ley hte 21 Rotor performance is calculated using the rotor efficiency Nrotor and rotor work is determined from the Euler turbomachinery equations 22 24 where AH is the change in Entropy across the rotor AH w rVa rVe i 22 AH C ATr 23 W mAH 24 After solving for all the flow quantities T AXI Blade generates a simple blade shape for use in the visualizations and 3D output This shape is dependent on the relative flow angles for the leading edge and trailing edge as well as the specified maximum thickness As can be seen from the vector triangles in figure 4 the camber line at the lea
15. ong the m cutplane 3 True Velocity Velocity of the flow as seen by an outside observer 4 Relative Velocity Flow velocity as seen by the blade row 5 Tangential Velocity Velocity component of the true velocity in the tangential direction swirl 6 Relative Tangential Velocity Velocity component of the relative velocity seen by the blade row in the tangential direction 7 Blade Row Velocity Tangential velocity of the blade row at the radius specified hub pitch or tip 8 Axial View Data Data from the axial view including meridional radial and axial velocity vectors 9 Graphic Cross section of the blade row at the radius specified hub pitch or tip Several other options are available for displaying the data output from T AXI Blade Figure 5 shows the Data Printout option available from the pull down menu There is also a Smith chart and a Loading vs Aspect Ratio chart available A recent addition to T Axi Blade is a formatted printout of common turbomachinery equations solved for the current blade design This page provides students with an easy way to find and fix mistakes in any hand calculations they are performing in addition to the T Axi Blade analysis T R Des Results PTin Pa TTin K PT_te Pa TT te K AreaH cm AreaT cm Z m Radius m U m s alpha deg be Le Tip Le Pitch Le Hub Te Tip Te Pitch Te Hub Figure 5 T AXI Blade Data Printout View Equations Page
16. own in 6 4 Phi This is the angle deg between the axial velocity vector and the meridional velocity vector 5 Graphic This is the graphical representation of the axial view of the blade 6 Vector Triangle This vector triangle represents the three flow components whose magni tudes are given axial velocity radial velocity and meridional velocity Figure 4 shows the pitch view output option from the T AXI Blade main window An overview of the data indicated with red numbers is shown below Leading Edge Trailing Edge Pitch Figure 4 T AXI Blade Pitch View 1 Values Table Table showing the magnitudes of the vectors and angles from the vector triangles e Vm Magnitude of meridional velocity shown as vector 2 e am Angle deg between meridional velocity 2 and absolute velocity 3 e Bm Angle deg between meridional velocity 2 and relative velocity of the flow as seen by the blade row 4 e V Magnitude of the absolute velocity shown as vector 3 e W Magnitude of the relative velocity of the flow as seen by the blade row shown as vector 4 e Vs Magnitude of tangential swirl velocity shown as vector 5 e We Magnitude of relative tangential swirl velocity of the flow as seen by the blade row shown as vector 6 e U Magnitude of velocity of the blade row shown as vector 7 e M a Mach number of the flow seen by the blade row shown as vector 4 2 Meridonal Velocity Velocity al
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