Thermo Equation Sheet Page 2
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1
2JET PROPULSION
1-2 DIFUSER:
2
2
2
V
V
V
⎛
⎞
⎛
⎞
−
2
1
q
w
h
h
;
0
C
(
T
T
)
1
;
⎜ ⎜
⎟ ⎟
⎜ ⎜
⎟ ⎟
−
=
−
+
=
−
−
12
12
2
1
p
2
1
2
2
⎝
⎠
⎝
⎠
(
k
) 1
−
P
P
T
P
k
⎛
⎞
r
2
;
2
2
2
=
⎜ ⎜
⎟ ⎟
=
P
P
T
P
⎝
⎠
r
1
1
1
1
2-3 COMPRESSOR:
(
k
) 1
−
P
P
T
P
k
⎛
⎞
r
P
r
P
;
3
;
3
3
3
=
⎜ ⎜
⎟ ⎟
=
=
3
p
2
P
P
T
P
⎝
⎠
r
2
2
4
2
3-4 COMBUSTION:
q
h
h
C
(
T
T
)
=
−
=
−
in
4
3
p
4
3
4-5 TURBINE:
w
w
;
h
h
h
h
;
(
T
T
)
(
T
T
);
=
−
=
−
−
=
−
comp
,
in
turb
,
out
3
2
4
5
3
2
4
5
(
k
) 1
−
P
P
T
P
k
⎛
⎞
r
5
;
5
5
5
⎜ ⎜
⎟ ⎟
=
=
P
P
T
P
⎝
⎠
r
4
4
4
4
5-6 NOZZLE:
2
2
2
V
V
V
⎛
⎞
⎛
⎞
−
6
5
6
q
W
h
h
;
0
C
(
T
T
)
;
⎜ ⎜
⎟ ⎟
⎜ ⎜
⎟ ⎟
−
=
−
+
=
−
+
56
56
6
5
p
6
5
2
2
⎝
⎠
⎝
⎠
(
k
) 1
−
T
P
k
⎛
⎞
6
6
⎜ ⎜
⎟ ⎟
=
T
P
⎝
⎠
5
5
w
(
V
V
)
V
−
p
exit
inlet
aircraft
Propulsion Efficiency
=
=
q
q
in
in
RANKINE
1-2 PUMP:
isentropic compression
h =
h
;
h
h
w
;
w
v
(
P
P
)
h
h
=
+
=
−
=
−
1
f
2
1
in
in
1
2
1
2
1
2-3 BOILER:
const. P heat addition
q
h
h
;
h =
h
at T & P for S.V.
=
−
in
3
2
3
sv
3-4 TURBINE:
isentropic expansion
s
s
−
4
f
w
h
h
;
x
;
h
h
x
h
=
−
=
=
+
out
3
4
4
4
f
4
fg
s
fg
4-1 CONDENSER:
const. P heat rejection
q
h
h
=
−
out
4
1
w
q
q
−
net
in
out
η
=
=
rankine
q
q
in
in
REFRIGERATION
1-2 COMPRESSOR:
isentropic compression
=
w
m
(
h
h
);
s
s
;
h
h
−
=
=
in
2
1
g
1
g
1
2-3 CONDENSOR:
const. P heat rejection
=
s =
s
;
h =
h
;
Q
m
(
h
h
)
−
3
f
H
2
3
2
1
3-4 THROTTLING:
throttling in an expansion device
h ≅
h
4
3
4-1 EVAPORATOR:
const. P heat absorption
=
Q
m
(
h
h
)
−
L
1
4
h
h
Q
−
2
s
1
C
.
O
.
P
.
L
η
=
=
comp
R
h
h
w
−
2
1
in
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