燃气轮机课程
设计
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--燃气轮机方向
燃气轮机方向
大气进气 进大气 气阀 排
气
涡压 G/M/F 轮气 机机 ~
燃烧室
一、单轴燃气轮机循环计算
1、设计参数
,,5T,288KP,1.013,10Pa
标准
excel标准偏差excel标准偏差函数exl标准差函数国标检验抽样标准表免费下载红头文件格式标准下载
状态进气条件:,; 00
,T,993K燃气初温:; 3
N,30KW燃机功率:; e
2、循环计算选取数据
,,2.1,压气机压比:; C
,,0.83,; 压气机效率:C
,,,0.96燃烧室燃烧效率:; B
,,,0.85涡轮效率:; T
,,0.99,机械效率:; m
,,,,,0.98,0.94,0.96,,压力损失:,,; inBout
,,,,,,0.88435,,,, ; inBout
,,,,,1.85714,,,涡轮膨胀比:; TC
漏气量:; ,,0
3、变比热循环计算
3.1、压气机进口参数
5,,,,,p,p,,0.95222,10PaT,T,288K由,,查
表
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1、2得: 10in10
00,ln, Iln,,I 1111
8354.27 -6.2958 1.71153 -0.002335
,,I,8354.27,6.2958,0.95222,8348.28KJ/Kmol, 1,,0
,,ln,,1.71153,0.002335,0.95222,1.70931; 1,,0
3.2、压气机出口参数
00,ln,,ln,,ln,,1.71153,ln2.1,2.45347由,查表1、2得: 21C
00I ln, T 2s2
355 2.44453 10306.64
356 2.45441 10335.85
,T,355.90K经插值得:; 2s
0,,,,I,10306.64,0.9,10335.85,10306.64,10332.93KJ/Kmol ; 2s,,0
00I,I,000,0s21; ,,,,,,,I,I,I,,I,10738.20KJ/KmolCsC2211,,000I,I21
查表1得:
0,I I T 22
369 10715.82 -3.6629
370 10745.07 -3.6382
,T,369.77K经插值得:; 2
5,,,p,p,,1.99966,10Pa由于得: 21C
,,I,10738.20,3.6439,1.99966,10730.91KJ/Kmol; 2,,0
,ln,,ln,,ln,,1.70931,ln2.1,2.45125; 21C
l,I,I,10730.91,8348.28,2382.63KJ/Kmol压气机压缩功:; C21
3.3、燃烧室出口参数
,T,993K已知燃气初温:, 3
5,,,p,p,,1.95970,10Pa , 32B
查表1得:
,,0,,1
0I 30079.99 32209.89 3
,I 1.6338 0.6872 3
,,,,I,30083.19KJ/KmolI,32211.24KJ/Kmol计算得:,; 33,,0,,1T,298K由查表1得: 1'
,,0,,1
0I 8645.24 8898.96 1'
,I -5.8852 -5.9498 1'
,,,,I,8633.71KJ/KmolI,8887.30KJ/Kmol计算得:,; 1'1',,0,,1
CH已知燃烧室所用燃料为航空煤油,分子式为,分子量816
HQ,44509KJ/KgM,112.21g/mol,低发热值。 fP
计算燃料摩尔系数:
57.17,II,,,,,,,32,,0,0,,H,,57.17,,61.17,,,,,,,,,,,,,MQ,IIIIfPB31'31',,0,,1,,0,,1
57.17,30083.19,10730.91,,,112.21,44509,0.96,57.17,30083.19,8633.71,61.17,32211.24,8887.30,,,,
,0.24082
1,过量空气系数:; ,,4.15248,
0.24082,燃料空气质量流量比:; ,,,0.016316,l14.760
,T,993K由查表1得: 3
00,IIln,,ln, Iln, 333333,,0.2 30329.43 1.4341 30532.24 6.30687 -0.000143 6.30659
,,0.3 30749.55 1.3363 30752.16 6.34105 -0.000137 6.34078
0,,,,I,30619.28KJ/KmolI,30622.01KJ/Kmol经插值得:,; 33,,0.24082,,0.24082
0,,,,ln,,6.32055ln,,6.32082 ,; 33,,0.24082,,0.24082
3.4、涡轮出口参数 00,ln,,ln,,ln,,6.32082,ln(2.1,0.88435),5.70179由,查表得: 43T
,,0.2,,0.3,,0.24082 T,851K
0ln, 5.68893 5.71665 5.70025 4
0I 25800.13 25970.77 25869.19 4s
,,0.2,,0.3,,0.24082 T,852K
0ln, 5.69357 5.72134 5.70491 4
0I 25832.97 26003.95 25902.76 4s
0,T,851.32K,,I,25880.34KJ/Kmol经插值得:,;4s4s,,0.24082
,,I,25881.34KJ/Kmol 4s,,0.24082
,ln,,ln,,ln,,5.70152; 43T
,p5,3; p,,1.05523,10Pa4,,T
00I,I,0000,34; ,,,,,,,I,I,I,I,,26591.18KJ/KmolTsT4334,,0.2408200I,Is34
查表1得:
,,0.2,,0.3,,0.24082 T,873K
0I 26524.27 26702.30 26592.94 4
,I 1.0661 0.9786 4
I26525.39 26703.33 26598.03 4
,T,873K由表数据可以计算得:, 4
0,,I,26598.03KJ/Kmol ; 4,,0.24082
l,I,I,30622.01,26598.03,4023.98KJ/Kmol涡轮膨胀功:; T34
3.5、综合性能参数
M,28.29g/mol已知空气分子量。 循环比功:
,,,,,l,,,1,,l,l,,,,1,0.016316,4023.98,2382.63,0.99,1689.94KJ/Kmol eTcm
l1689.94,e,循环热效率:; ,,,8.23%eH,QM0.016316,44509,28.29P
NM30,28.29e; 空气流量:q,,,0.502Kg/sml1689.94e
B,q,0.502,0.016316,1000,8.19g/s,燃油流量:。 em
二、离心压气机叶轮设计计算
1、设计参数
D,0.11m叶轮出口直径:; 2
D1t叶轮轮径比:, ,0.7,D,0.077m1tD2
D1h , ,0.2,D,0.022m1tD2
22D,Dht11 ; D,,0.0566mm12
n,54000r/min叶轮转速:;
nD,1m叶轮入口圆周速度:; u,,160.03m/s160
nD,2叶轮出口圆周速度:u,,311.02m/s; 260
,,,0.83,,压气机多变效率:; nc
mkm,1.525解方程得:多变指数; ,,nm,1k,1
2、叶轮进口静参数计算
P,5,30P,P,1.013,10PaT,T,288K,,。 已知,,,1.2256Kg/m00000RT0
PP,01,mm,,,10,c,98.88m/s,1P1,,3,RT1,1.1876Kg/m,,,1,1列方程组: ,,,2T,283.13Kkck1,,,1RT,,RT11,,P,96507Pak,12k,11,,22,,,q,cD,D,,m111t1h4,
3、确定理论能量头
多变压缩功:
m10.525,,,,,mR1.525m1.525,,,,l,T,,1,,287,283.13,2.1,1,68.688KJ/Kgcs1c; ,,,,m,10.525,,,,
l68.688n实际压缩功:; l,,,82.756KJ/Kgc,0.83n
l82.756c理论能量头:(已知摩擦损失和泄h,,,81.134KJ/Kgth,,1,,1,0.02vr
,,,,0.02露损失之和); vr
4、叶轮出口静参数计算
h81134,thT,369.77Kb,10mm已知,,出口周向速度。 c,,,260.86m/s22uu311.022
',PP10,,mm',,0,c90.40m/s,1,r2','3,P'1,,1.6068Kg/m,,1列方程组 ,RT1',,,',1T,331.83K1,,22c,ckk'',ur22,,P,153030PaRT,,RT112,,k,12k,1',q,Dbcmr122,,,
2222c,c,c,90.40,260.86,276.08m/s压气机动叶出口绝对速度:; ru222
5、速度三角形
叶轮入口:
::,,90,,31.71c,98.88m/su,160.03m/sw,188.11m/s,,,,; 11111叶轮出口:
::,,19.11,,60.98c,276.08m/su,311.02m/sw,103.38m/s,,,,; 22222
c2叶轮出口马赫数; Ma,,0.762'kRT1
6、叶型设计
222222w,wc,cu,u122121叶轮轮缘功:; l,,,,81132.35J/Kgu222
22cc,21叶轮反动度:; ,,1,,0.591l2u
,,,,,,,12sin,,,,,2,,,,N,Integer,17转子叶片数:; KR,,,0.2lnDD,,1m2
,,,,
22DD,,,,21m,,,,,22,,,,R,,0.4287圆弧半径计算:; CDD,,m21,,2cos,cos,,2122,,
2DD,,,,222,,,2cos,,0.4049圆心位置计算:RRR; ,,,,0cc222,,,,
三、叶片扩压器设计计算
,',T,T叶片扩压器内可以近似绝热摩擦流,则进出口总温。 12已知叶片扩压器进口参数如下:
,'':''',,,19.11c,276.08m/sT,331.83KP,153030PaT,T,369.77K,,,,,112111'3,,1.6068Kg/m; 1
'c'1进口马赫数,说明进口气流为亚音速,扩压器为Ma,,0.76,11'kRT1
渐扩的,气流在其中流动,速度逐渐降低,压力逐渐升高。
k,'k1,2,Pk,1,,''51,1,Ma,1.466,P,2.2436,10Pa解方程; ,,11'P2,,1
叶片扩压器出口参数如下:
,P,5,,32P,1.99966,10PaT,369.77K,,; ,,,1.8843Kg/m222,RT2
cc,100m/s取出口速度为接近压气机进口速度; 12
2kkc,2解方程; RT,RT,,T,364.79K222k,1k,12
c2出口马赫数:; Ma,,0.2612kRT2
1,k,1,k,1,,232解方程,1,Ma,1.034,,,1.8216Kg/m; ,,222,,,2
,'P,1扩压器内的流动损失:; l,TRln,12.22KJ/Kg2f,P2
bb,9.4mm取叶片扩压器叶高略小于离心叶轮动叶叶高,即,叶片b22
',,,,,,12.89,32扩压器出口角; 21
'''',,,,,,cbDcbDsin,sin111122222
''',,,,Dcbsin276.08,sin19.11101.6068解方程 2111,,,,,,1.6',Dc,,b,sin100,sin329.41.821612222
'D,0.11mD,0.176m由,得出叶片扩压器外径; 21
四、涡轮叶轮的设计计算 1、设计参数
,,,,q,1,,q,1,0.016316,0.502,0.510Kg/s涡轮叶轮流量:; fm
,,,1.85714膨胀比:; T
,,5T,993Kp,1.95970,10Pa燃气初参数:, 33
2、确定涡轮等熵焓降
h,I,I,30622.01,25881.34,4740.67KJ/Kmol; Ts34s
3、求理论假象速度
22,4740.76,1000c0由求解得:; ,hc,2h,,578.98m/sts0ts228.29
,,0.554、选定涡轮反动度 c,c1,,,388.39m/s; 1s0
,,0.955、选定导叶速度系数 c,c,368.97m/s,; 11s
,,,156、选取进口绝对气流角; 1
u,0.67、选取特性速比 u,uc,347.39m/s; 10
8、确定入口转轮直径
60u60,347.39n,D1解方程得:; ,D,,,0.12mu160,,n54000
D2t, 取叶轮轮径比:,0.7,D,0.084m2tD1
D2h , ,0.2,D,0.024m2tD1
22D,Dht22 ; D,,0.0617mm22
,222涡轮出口通流面积:; A,,,D,D,5089.38mmth2249、确定入口速度三角形
,,,15c,368.97m/su,347.39m/s已知,,; 111
22w,c,u,2cucos,,95.92m/s; 111111
cw,11,,84.61解方程得: ,1sin,sin,11
10、确定出口速度三角形
nD54000,,0.0617,,,2m,,90已知,; u,,,174.45m/s2260602222u,uw,w2112s,22w,321.28m/s由反动度解得:; ,,,0.552s2c0
2
w,w,0.95,321.28,305.32m/s,; 22s
22c,w,u,250.57m/s; 222
,,u,2,,; ,,arccos,55.152,,w2,,
w2加速因子: ,,,3.18w1
11、计算出口通流面积
涡轮出口静参数计算如下:
,,5k,1.33R,287KJ/KgT,873Kp,1.05523,10Pa已知,,,; 44
2kkc,2由 RT,RT,,T,845.86K444k,1k,12
,P,34 ,,,0.4368Kg/m4,RT4
c2出口马赫数: Ma,,0.444kRT4
1,k,1,k,1,,234,1,Ma,1.100,,,0.3971Kg/m解方程; ,,422,,,4
''2A,5125.56mmq,,cA,0.510Kg/s求解流量方程得: f42
'由于与相差不大,因此通流面积校核符合几何和气动条件,涡轮AA
叶轮设计合理。
五、参考文献
[1]严家騄,烃类燃料的燃气热力性质表,科学出版社,1989年12月
[2]刘光宇,船舶燃气轮机装置原理与设计,哈尔滨船舶工程学院出
版社
[3]胡俊,航空叶片机原理,哈尔滨船舶工程学院出版社,2005年10
月