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http://www.hnjet.com/english/productinfo.asp?ID=5
A. General
The micro-turbojet engine HN-40-65(hereafter referred to as the turbojet) is a highly reliable, low-cost, single-shaft turbine jet engine. It consists of centrifugal compressor, bearing lubricating system, annular firebox, radial turbine, simple convergent nozzle and electron fuel controller.
The thrust of HN-40-65 is 650N .
B. Description
The engine HN-40-65 consists of the following six parts:
a) Inlet assembly: The S/A consists of an inlet duct which is taken the shape of hyperbola and a center body located at the rear of the inlet duct. The inlet duct conducts the air into the compressor with less pressure drop. The center body is supported by three rods, apart from each other by 120°. The center body contained a starting motor.
b) Compressor: The S/A consists of centrifugal rotor, radial diffuser and axial diffuser. The clip bush of the bearings and the bearing lubricating system are fixed at the rear of the diffuser.
c) Firebox: The S/A consists of main fuel supply system, starting fuel supply system, igniting device, flame canister and the housing.
d) Turbine: The S/A consists of a guided ring and a radial turbine.
e) Nozzle: It is a simple convergent nozzle.
f) Fuel control system: The S/A consists of Digital Fuel Electronic Control Unit (ECU) and fuel pump.
C. Characteristics
1. Physical Data
2. Technical Data
3. Operation limits
Max. flight height: 7620m
Max. flight velocity: 0.8Ma
Min. working temperature: -40℃
Max. working temperature: +35℃
4. Applicable fluid
4.1 Fuel
RP-3 Aero fuel
High-density hydrocarbon fuel（National Production）
4.2 Lubricating oil
ESSO 2T
Aeroshell 540
Aeroshell 500
5. Igniter
Electrothermal igniter (pyrotechnic igniter can be used for special purpose)
6. Starting
6.1 Electrical starting
A starting motor is located in the center of the inlet assembly. It can be
driven easily with 12VDC power and started the engine all right.
6.2 Windmill starting
As the windmill starting is more simply and reliable during flight, it is widely used on missiles. Windmill starting is suitable for the engine HN-40-65 which has good windmill performances. Refer to Fig.1 for the relationship between windmill speed of engine HN-40-65 and air speed (M), The curve is independent of the altitude
Fuel Electronic Control Unit (ECU)
The engine HN-40-65 contains a Digital Fuel Electronic Control Unit (ECU). The 12V (or 24V) current is supplied by battery or DC power source. The input signals include the rotate speed of engine (n), the pressure (P2) at the compressor outlet, the exhaust temperature (T4) and order signal (simulation or digital signal). The output signal is the pulsed voltage signal to control the fuel supply.
8. Overload
Momentary overload at X axis while accelerating: 7~10g;
Momentary overload at X axis while decelerating: 20g;
Y axis and Z axis (respective): 50g;
Max. yaw overload: 50g.
9. Limits
9.1 Max. allowable speed:92000r/min
9.2 Max. allowable exhaust temperature:760℃
9.3 Continuous operating time:
The time is more than 2 hours being at the max. allowable speed.
10. Life： Maintenance life: 20h.
A. General
The micro-turbojet engine HN-40-45(hereafter referred to as the turbojet) is a highly reliable, low-cost, single-shaft turbine jet engine. It consists of centrifugal compressor, bearing lubricating system, annular firebox, radial turbine, simple convergent nozzle and electron fuel controller.
The thrust of HN-40-45 is 450N .
B. Description
The engine HN-40-45 consists of the following six parts:
a) Inlet assembly: The S/A consists of an inlet duct which is taken the shape of hyperbola and a center body located at the rear of the inlet duct. The inlet duct conducts the air into the compressor with less pressure drop. The center body is supported by three rods, apart from each other by 120°. The center body contained a starting motor.
b) Compressor: The S/A consists of centrifugal rotor, radial diffuser and axial diffuser. The clip bush of the bearings and the bearing lubricating system are fixed at the rear of the diffuser.
c) Firebox: The S/A consists of main fuel supply system, starting fuel supply system, igniting device, flame canister and the housing.
d) Turbine: The S/A consists of a guided ring and a radial turbine.
e) Nozzle: It is a simple convergent nozzle.
f) Fuel control system: The S/A consists of Digital Fuel Electronic Control Unit (ECU) and fuel pump.
C. Characteristics
1. Physical Data
2. Technical Data
3. Operation limits
Max. flight height: 7620m
Max. flight velocity: 0.8Ma
Min. working temperature: -40℃
Max. working temperature: +35℃
4. Applicable fluid
4.1 Fuel
RP-3 Aero fuel
High-density hydrocarbon fuel（National Production）
4.2 Lubricating oil
ESSO 2T
Aeroshell 540
Aeroshell 500
5. Igniter
Electrothermal igniter (pyrotechnic igniter can be used for special purpose)
6. Starting
6.1 Electrical starting
A starting motor is located in the center of the inlet assembly. It can be driven easily with 12VDC power and started the engine all right.
6.2 Windmill starting
As the windmill starting is more simply and reliable during flight, it is widely used on missiles. Windmill starting is suitable for the engine HN-40-45 which has good windmill performances. Refer to Fig.1 for the relationship between windmill speed of engine HN-40-45 and air speed (M), The curve is independent of the altitude.
Standard Temperature & Pressure
Temperature: 15 Degrees Celsius, Pressure: 1013 Mbar
Engine diameter
Engine length（Electric start ）
Engine weight（Electric start ）
Thrust（Max. rpm）
Thrust（Idle rpm）
Pressure ratio（Max. rpm）
Mass flow（Max. rpm）
Maximum allowed rpm
Normal exhaust gas temperature
Fuel types
http://www.hnjet.com/english/productinfo.asp?ID=5
Price: USD2,4000.00
A. General
The micro-turbojet engine HN-40-65(hereafter referred to as the turbojet) is a highly reliable, low-cost, single-shaft turbine jet engine. It consists of centrifugal compressor, bearing lubricating system, annular firebox, radial turbine, simple convergent nozzle and electron fuel controller.
The thrust of HN-40-65 is 650N .
B. Description
The engine HN-40-65 consists of the following six parts:
a) Inlet assembly: The S/A consists of an inlet duct which is taken the shape of hyperbola and a center body located at the rear of the inlet duct. The inlet duct conducts the air into the compressor with less pressure drop. The center body is supported by three rods, apart from each other by 120°. The center body contained a starting motor.
b) Compressor: The S/A consists of centrifugal rotor, radial diffuser and axial diffuser. The clip bush of the bearings and the bearing lubricating system are fixed at the rear of the diffuser.
c) Firebox: The S/A consists of main fuel supply system, starting fuel supply system, igniting device, flame canister and the housing.
d) Turbine: The S/A consists of a guided ring and a radial turbine.
e) Nozzle: It is a simple convergent nozzle.
f) Fuel control system: The S/A consists of Digital Fuel Electronic Control Unit (ECU) and fuel pump.
C. Characteristics
1. Physical Data
No.
Description
Data
1
Max. length (mm)
430
2
Max. OD (mm)
205
3
Net weight (kg)
8.6
2. Technical Data
No.
Description
Data
1
Max. thrust (N)
650
2
Nominal fuel consumption (kg/daN.h)
1.44
3
Airflow rate(kg/s)
1.56
4
Pressure ratio
3.85:1
5
Max. Rotate Speed (rpm)
79000
6
Exhaust temperature (℃)
520
3. Operation limits
Max. flight height: 7620m
Max. flight velocity: 0.8Ma
Min. working temperature: -40℃
Max. working temperature: +35℃
4. Applicable fluid
4.1 Fuel
RP-3 Aero fuel
High-density hydrocarbon fuel（National Production）
4.2 Lubricating oil
ESSO 2T
Aeroshell 540
Aeroshell 500
5. Igniter
Electrothermal igniter (pyrotechnic igniter can be used for special purpose)
6. Starting
6.1 Electrical starting
A starting motor is located in the center of the inlet assembly. It can be
driven easily with 12VDC power and started the engine all right.
6.2 Windmill starting
As the windmill starting is more simply and reliable during flight, it is widely used on missiles. Windmill starting is suitable for the engine HN-40-65 which has good windmill performances. Refer to Fig.1 for the relationship between windmill speed of engine HN-40-65 and air speed (M), The curve is independent of the altitude
Fig. 1 Windmill performances of HN-40-65
Fuel Electronic Control Unit (ECU)
The engine HN-40-65 contains a Digital Fuel Electronic Control Unit (ECU). The 12V (or 24V) current is supplied by battery or DC power source. The input signals include the rotate speed of engine (n), the pressure (P2) at the compressor outlet, the exhaust temperature (T4) and order signal (simulation or digital signal). The output signal is the pulsed voltage signal to control the fuel supply.
8. Overload
Momentary overload at X axis while accelerating: 7~10g;
Momentary overload at X axis while decelerating: 20g;
Y axis and Z axis (respective): 50g;
Max. yaw overload: 50g.
9. Limits
9.1 Max. allowable speed:92000r/min
9.2 Max. allowable exhaust temperature:760℃
9.3 Continuous operating time:
The time is more than 2 hours being at the max. allowable speed.
10. Life： Maintenance life: 20h.
A. General
The micro-turbojet engine HN-40-45(hereafter referred to as the turbojet) is a highly reliable, low-cost, single-shaft turbine jet engine. It consists of centrifugal compressor, bearing lubricating system, annular firebox, radial turbine, simple convergent nozzle and electron fuel controller.
The thrust of HN-40-45 is 450N .
B. Description
The engine HN-40-45 consists of the following six parts:
a) Inlet assembly: The S/A consists of an inlet duct which is taken the shape of hyperbola and a center body located at the rear of the inlet duct. The inlet duct conducts the air into the compressor with less pressure drop. The center body is supported by three rods, apart from each other by 120°. The center body contained a starting motor.
b) Compressor: The S/A consists of centrifugal rotor, radial diffuser and axial diffuser. The clip bush of the bearings and the bearing lubricating system are fixed at the rear of the diffuser.
c) Firebox: The S/A consists of main fuel supply system, starting fuel supply system, igniting device, flame canister and the housing.
d) Turbine: The S/A consists of a guided ring and a radial turbine.
e) Nozzle: It is a simple convergent nozzle.
f) Fuel control system: The S/A consists of Digital Fuel Electronic Control Unit (ECU) and fuel pump.
C. Characteristics
1. Physical Data
No.
Description
Data
1
Max. length (mm)
340
2
Max. OD (mm)
154
3
Net weight (kg)
4.75
2. Technical Data
No.
Description
Data
1
Max. thrust (N)
450
2
Nominal fuel consumption (kg/daN.h)
1.52
3
Airflow rate(kg/s)
0.95
4
Pressure ratio
3.45:1
5
Max. Rotate Speed (rpm)
88000
6
Exhaust temperature (℃)
600
3. Operation limits
Max. flight height: 7620m
Max. flight velocity: 0.8Ma
Min. working temperature: -40℃
Max. working temperature: +35℃
4. Applicable fluid
4.1 Fuel
RP-3 Aero fuel
High-density hydrocarbon fuel（National Production）
4.2 Lubricating oil
ESSO 2T
Aeroshell 540
Aeroshell 500
5. Igniter
Electrothermal igniter (pyrotechnic igniter can be used for special purpose)
6. Starting
6.1 Electrical starting
A starting motor is located in the center of the inlet assembly. It can be driven easily with 12VDC power and started the engine all right.
6.2 Windmill starting
As the windmill starting is more simply and reliable during flight, it is widely used on missiles. Windmill starting is suitable for the engine HN-40-45 which has good windmill performances. Refer to Fig.1 for the relationship between windmill speed of engine HN-40-45 and air speed (M), The curve is independent of the altitude.
Fig. 1 Windmill performances of HN-40-45
7. Fuel Electronic Control Unit (ECU)
The engine HN-40-45 contains a Digital Fuel Electronic Control Unit (ECU). The 12V (or 24V) current is supplied by battery or DC power source. The input signals include the rotate speed of engine (n), the pressure (P2) at the compressor outlet, the exhaust temperature (T4) and order signal (simulation or digital signal). The output signal is the pulsed voltage signal to control the fuel supply.
8. Overload
Momentary overload at X axis while accelerating: 7~10g;
Momentary overload at X axis while decelerating: 20g;
Y axis and Z axis (respective): 50g;
Max. yaw overload: 50g.
9. Limits
9.1 Max. allowable speed:103000r/min
9.2 Max. allowable exhaust temperature:780℃
9.3 Continuous operating time:
The time is more than 2 hours being at the max. allowable speed.
10. Life： Maintenance life: 20h.
HN-40-20
Price: USD1,6000.00
Temperature: 15 Degrees Celsius, Pressure: 1013 Mbar
Description
Data
Unit
130
mm
374
mm
2900
gram
200
N
10
N
4:1
450
gram/sec
108,000
rpm
700
℃
kerosene/paraffin/jet A-1
