AGMA 95FTM7-1995 Experimental and Analytical Assessment of the Thermal Behavior of Spiral Bevel Gears《螺旋伞齿轮的热行为的实验和分析评估》.pdf

《AGMA 95FTM7-1995 Experimental and Analytical Assessment of the Thermal Behavior of Spiral Bevel Gears《螺旋伞齿轮的热行为的实验和分析评估》.pdf》由会员分享，可在线阅读，更多相关《AGMA 95FTM7-1995 Experimental and Analytical Assessment of the Thermal Behavior of Spiral Bevel Gears《螺旋伞齿轮的热行为的实验和分析评估》.pdf（21页珍藏版）》请在麦多课文档分享上搜索。

1、STD.AGMA S5FTM7-ENGL 1775 Ob87575 0004718 831 S 95FTM7 Experimental and Analytical Assessment of the Thermal Behavior of Spiral Bevel Gears by: Robert Handschuh, NASA Lewis Research Center and Thomas Kicher, Case Western Reserve University c American Gear Manufacturers /? TECHNICAL PAPER Experimenta

2、l and Analytical Assessment of the Thermal Behavior of Spiral Bevel Gears Robert Handschuh, NASA Lewis Research Center and Thomas Kicher, Case Western Reserve University The statements and Opinions contained herein are those of the author and should not be construed as an official action or opinion

3、of the American Gear Manufacturers Association. Abstract An experimental and analyticai study of Spirai bevel gears operating in an aerospace environment has been performed. Tests were conducted within a closed loop test stand at NASA Lewis Research Center. Tests were conducted to 537 kW (720 hp) at

4、 14 400 rpm. The effects of various operating conditions on spirai bevel gear steady state and transient temperaturearepresented Aiso,athreedim ensional analysis of the thermai behavior was conducted using a nonlinear fnite element analysis computer code. The analysis was compared to the experimenta

5、l results attained in this study. The results agreed well with each other for the cases compared and were no more than 10 percent different in magnitude. Copyright O 1995 American Gear Manufacturers Association 1500 King Street, Suite 201 Aiexandria, Vnginia, 2,2314 October, 1995 ISBN. 1-55589-65 r*

6、 3- Jet location 1 25 1 23 45 Lubricant jet location Figure 9.-Effect of lubricant jet location on pinion thermocouple measurements for two flow rates at 526-538 kW (705-721 hp). Upper symbol is for 24 cm3/sec (0.38 gpm) and lower symbol is for 49 cm%ec (0.77 gpm). STD-AGMA 75FTM7-ENGL 1775 D Ob8757

7、5 0004732 LOI D Position of measurement 1 2 3 4 5 6 7 R 10 15 20 25 30 Infrared path 7 - r Pinion tooth tip Pmxmity Probe Probesaturated k- 3oo.-n+ Drnfiin nArl I flux applied Figure 15.4ontact ellipse number 9 of 15, shown plotted on the entire concave profile grid. _ STD-AGHA 95FTM7-ENGL 1995 9 Ob

8、87575 000973b 857 Heel 200 190 9 180 E 8 3 c E E 8 170 , 160 1 50 One revolution 4 b I I I I I I I O 100 200 300 400 500 600 800 Increment after time averaged solution Figure 16.4cve profile grid point location and temperature transient. STDmAGMA 75FTM7-ENGL 1995 m Ob87575 0004737 773 m X Figure 17.

9、-Heat flux increment 13, temperature OC 160 7 150 - 140 - 130 - 9 g 120 3 e: io! - a E 110 - 100 - Anaiysis condition O AS shown below; Ambient temperature = 38 OC 0 Cnivasideh=3383 V AS shown below; Ambient temperature = 60 “c (h - Heat transfer convection coefficient) V AS shown below; h = O (Wh2.

10、 OC) fw top, toa, heel Experimental conditions 0 Jet Wo before mesh on gear; 1.38 MPa; 38 OC oil inlet temperature W Jet into mesh; 0.34 MPa; 38 OC ail inlet temperature - 70 I I I I I TOP Root Toe Heel (a) Comparison of hwits. h544!i dmie- 7 hr16 I slice Figurn 18.-CompaMon of kdk tnmsunnants from themiocouples to Eme9vemged boundary condion analytical results.