Dr Rafea_compressors-turbomachinery .pdf

Dr Rafea_compressors

1. Dynamic Compressors

5. Axial, mixed and centrifugal compressors
Centrifugal

6. Axial, mixed and centrifugal compressors

7. Centrifugal
Compressor
Axial Compressor
Global looking of main internal component

12. Applications of dynamic compressors
Gas turbines
Jet engines
Super and turbochargers
Transportations (Aero-planes)
Various industrial applications
blast furnaces
wind tunnels
wastewater treatment
and air separation

13. Industrial Gas Turbine
13

14. Turbocharger
Turbine exit
Compressor inlet

15. Industrial
three stage
centrifugal
compressor

16. Compressor components

17. GE Gas turbine components and operation

https://www.youtube.com/watch?v=pEnlUpG9_t0

18. GT 2 Rotor Balancing

https://www.youtube.com/watch?v=bZYZW3WiiFs

19. Compressor Rotor II - Turbine Engines A
Closer Look

https://youtu.be/xknOx-6_zqU

20. Compressors - Turbine Engines A Closer Look

https://www.youtube.com/watch?v=CXSi4GXUojo

21. How to balance a compressor pt. 3 - A Closer
Look

https://www.youtube.com/watch?v=od_-u-BPjBk

22. How to balance a compressor pt. 4 - A Closer
Look

https://www.youtube.com/watch?v=eY_1OtdnbeI

23. Blade Manufacturing

24. 5-Axis Machining, 5-Axis Mill

https://youtu.be/xZOiNdkJ8SU

25. Blade machining by Sandvik Coromant

https://youtu.be/lmws9RRCct8

26. Balancing

27. ► CIMAT high speed turbocharger core
balancing machine (Burke Porter Group)

https://www.youtube.com/watch?v=Ecb9WZnhtos

28. ✅ CIMAT: turbocharger rotor balancing machine ✅Polymer✅
BALANCEADORA DE ROTORES✅WYWAŻARKA WIRNIKÓW

https://youtu.be/nOYBkx19uSQ

29. Axial flow compressor

31. Elementary Theory
•Total and static pressure and temperature rise across the rotor blades due to addition of
external work.
•Absolute flow undergoes acceleration across rotor blade rows.
•There is flow diffusion across stator blade rows, converting kinetic energy into
pressure.
•The design pressure rise is achieved in a number of stages.

32. Axial compressor
•The stator blades are attached to the
casing.
•The rotor blades force the gas to
move, impart pressure and velocity

•As the gas flows through an axial
compressor it occupies less volume
increasing its pressure.
•The rotor blades increase velocity and
stator blades convert it to pressure

33. Example of Axial compressors

34. Different axial
flow compressor
blades

35. A typical multistage axial flow
compressor (Rolls-Royce, 1992).

36. Axial compressor construction

37. An axial flow compressor stage
37

38. Multi-stage axial compressor

40. Compressor stage

41. The First Two Stages Of An Axial Compressor

42. PEMP
RMD 2501
Single Stage Axial
Compressor
Components of Axial Compressor
Rotor Stator
•Rotor
•Stator
•Casing
•Shaft
Applications of axial

compressor
•Gas turbine
Flow
•Turbocharger
•Process industry

43. Multistage Axial
Compressor
01 43
@ M.S.Ramaiah School of Advanced Studies

44. Variation of enthalpy, velocity, and pressure through
an axial flow compressor

45. Mollier diagram for an axial turbine stage

Mollier diagram for an axial compressor
stage

47. Axial Flow Compressors
static enthalpy rise in rotor
static enthalpy rise in the stage h
s

h
r
Degree of reaction
R is the ratio of static enthalpy in rotor to static enthalpy
rise in stage
R 

48. Un-symmetrical Blading
If R > 0.5, then β
2 > α
1 and
the velocity diagram is
skewed to the right. The static
enthalpy rise in the rotor
exceeds that in the stator (this
is also true for the static
pressure rise).
If R < 0.5, then β
2 < α
1 and the
velocity diagram is skewed to
the left. The stator enthalpy
(and pressure) rise exceeds
that in the rotor.

49. Axial Flow Compressors
o1 o1
s
(tan 
1  tan 
2 )
2 2
 tan
1  tan 
1  tan
R
pressurerise per stage
tan 

UC
a
p
a
T
 [1

s T
s
]
 /( 1)
p

p
o3
c
C
W  m U (C
w1  C
w1 )
 m UC
a (tan
2  tan
1 )
 m UC
a (tan 
2  tan 
1 )
T
os  T
o3  T
o1  T
o 2  T
o1
U

50. Axial flow
compressor
map

51. Axial flow compress
map

52. Axial flow
compress map

53. Centrifugal compressor

55. Industrial
three stage
centrifugal
compressor

56. Centrifugal Compressor

57. Multi Stage Centrifugal Compressor

58. Multi Stage Centrifugal Compressor

59. Types of entry inducer systems

60. Centrifugal Compressor

61. Centrifugal Compressor

62. Centrifugal Compressor

63. Multi Stage Centrifugal Compressor

64. Multi Stage Centrifugal Compressor

65. Multi Stage
Centrifugal
Compressor

66. Centrifugal
compressor
stage and
velocity
diagrams at
impeller entry
and exit.

67. Centrifugal compressor components

68. Centrifugal compressor

69. Centrifugal compressor

70. Centrifugal
compressor

71. Centrifugal compressors
Blades force air in the impeller to move. The impeller
adds both velocity and pressure to air.

Gas passes from the diffuser into the volute. The
conversion from velocity to pressure continues.

72. Centrifugal compressors

73. Compressor Impeller

74. Back to back impeller Split impeller

75. Various types of compressor blading

76. Types of Centrifugal Compressor Impeller
Radial exit impeller
Back swept impeller
Forward swept impeller
0
2
  90
0
2   90
0
2
  90
Forward sweep V
 < U
2
Radial exit V
 = U
2
Backward sweep V
 > U
2
Impeller with splitter blades
Impeller with diffuser

77. Centrifugal compressor stage

79. Compressor construction
Casing Design
•Vertically Casing requires less sealing

•Horizontally casing has easier access

80. Typical centrifugal compressor performance
characteristics.

81. Typical centrifugal compressor performance
characteristics.

82. Typical centrifugal compressor performance
characteristics.

83. Typical centrifugal compressor performance
characteristics.

84. Axial-flow compressor map
Centrifugal compressor map
Instability line
Instability line

85. Comparisons between axial and centrifugal
compressor

87. Rotating stall and surge

89. Tank
System valve

97. Tank
Interstage bleed valve
Stall bleed valve Surge bleed valve
System valve

100. Part-Span rotating stall with different stalled cells
Full-Span rotating stall with different stalled cells

101. Transient response of system in surge Transient response of system in stall

104. Stage losses in Axial Flow
Compressor
Profile Loss: This loss occurs due to growth of boundary layer & it separation on
blade profile. Separation of boundary layer occurs when adverse pressure gradient
on surface becomes too steep, this increases profile loss.
Shock in rotor losses : the inlet of rotor blades should be gradually expanded
to sustain weak oblique shock wave , if the blades are blunt the bow shock
wave will occurs and the losses will be higher .

105. incidence losses : occurs due to the off-design condition when the flow air enter
to impeller at positive incidence angle causes reduction in flow because of
instantaneous change of velocity at the blade in let comply with blade inlet
angle.
Disc friction losses : this losses result from frictional torque on the back surface
of the rotor sometimes called (external losses).
Clearance and leakage losses: Certain minimum clearances are necessary
between the impeller shaft and the casing and between the outlet periphery of
the impeller eye and the casing. The leakage of gas through the shaft clearance is
minimized by employing glands.

106. Secondary Loss: This loss occurs due to secondary flows in blades passage as shown
in fig. In axial flow compressor certain secondary flows are produced by combined
effect of curvature & boundary layer. It is produced when a stream-wise component
of velocity is developed from deflection of an initially sheared flow.
19

107. Tip Leakage Loss: - Tip clearance between blades & casing causes leakage of fluid
from pressure side to suction side of blades as shown in fig. Therefore scraped up
boundary layer of casing increases tip leakage & generates additional secondary
flow.
20