WO2023166534A1

WO2023166534A1 - Hyperboost engine strap

Info

Publication number: WO2023166534A1
Application number: PCT/IN2023/050396
Authority: WO
Inventors: Aditya Sharma
Original assignee: Aditya Sharma
Priority date: 2023-03-10
Filing date: 2023-04-22
Publication date: 2023-09-07

Abstract

Think above the speed of sound and engineering which breaks that barrier of sound speed and gives us supersonic and hypersonic speeds many cruise missiles and air-to-air missiles work on supersonic speed mostly between Mach 2.5 to Mach 4 using ramjet or solid boosters but still because of several factors like aerodynamic heat, materials, propulsion, stability, and control it is hard to achieve hypersonic speed. Apart from all the technical challenges many engineers and researchers working on scramjet which can operate above Mach 5 or 6 and gives us the potential for high-speed flight and space explorations. So, as we can see the limitation between Mach 2.5 to Mach 5 which mostly solid boosters use, we introduce an idea called HyperBoost Straps these are the straps that will help to operate from Mach 3 to Mach 5 for existing cruise and air to air missiles to achieve an extra thrust which will increase max. speed and range. Whenever we think above the speed of sound and Mach numbers, we have only 2 names in mind Ramjet and Scramjet engines that are used for the propulsion of aircraft at high speeds. The main difference between them is the speed range at which they operate efficiently. But now we are introducing a new engine design and working which will work between Ramjet and Scramjet speed range which is Mach 3 to Mach 5 and these engine straps can work between Alt of 5 Km to 15 Km (compressible flow calculations are attached).

Description

HyperBoost Engine Strap

Aditya Sharma (Individual Researcher) Jaipur, Rajasthan, India Introduction: -

Whenever we think above the speed of sound and Mach numbers, we have only 2 names in mind Ramjet and Scramjet engines that are used for the propulsion of aircraft at high speeds. The mam difference between them is the speed range at which they operate efficiently.

But now we are introducing a new engine design and working which will work between Ramjet and Scramjet speed range which is Mach 3 to Mach 5 and these engine straps can work between Alt of 5 Km to 15 Km (compressible flow calculations are attached). The difference table of Ramjet, Scramjet, and HyperBoost engines are as follows: -

SUBSTITUTE SHEET (RULE 26)

Design: -

HyperBoost Strap Dimension: - 1 m(length) * 16 Cm(width) * 19 Cm (Height)

Fig i : - 2D design / Schematic representation of HyperBoost Straps

Material used: - Titanium (body) with 1940’k melting point

Tungsten (Combustion chamber and joints) with a 3695’k melting point

Weight: - Body by titanium weight of around 10.27 Kg. Combustion and nearby tungsten weight around 1.7KgKerosene bubbled with H2 used as a fuel around 4,63 Kg. and electronics equipment used around 2.5Kg.

The total rough idea of Weight: - 19 Kg - 19.5 Kg.

Working Range: - At Alt 5Km. from Mach 3.2 to Mach 5.3

At Alt lOKm from Mach 2.9 to Mach 5

At Alt 15Km from Mach 2.9 to Mach 4.7

Time Range: - 5.1 Sec to 770 Sec.

Avg Run Time: - 18 sec to 155 sec.

Inlet: -

Here in HyperBoost design, we use 3 oblique shock flatted ramp designs from which 2 are internal ramps with oblique shock angel at 10’ each and one is external with a strongly oblique angle of 20’. The boundary layer, Max wave angle, and Drag area will be as follows: -

Fig 2: - Boundary layer and drag area

The drag will be as follow: -

Total Drag D = DI + D2 + D3

The design of the inlet will be as follows: -

SUBSTITUTE SHEET (RULE 26) Fig 3: - 3D view of inlet

Fuel Mixing Chamber: -

In the HyperBoost engine strap, we use a new structure of fuel injector design which is helpful to achieve mixing efficiency of more than 90% also for fuel mass flow it easily operatesfrom 5gm/sec to 950gm/sec. and due to this unique design velocity loss is less than 7%. The design of the mixing chamber and 8 injectors in 5 states are placed like that: -

Fig.4: - Schematic representation of Mixing Chamber and injector design

For the injector, we used a swallow prism design with 6 fuel inject holes which spread fuel in both directions and this design is 2 cm *2 cm*2 cm.

One diffuser will be placed just at the entry of the mixing chamber from the inlet for solving the problem of air stuck due to shock waves and the high velocity of air this will remove extra air from the mixing chamber and allow the flow of air to continuously.

Fig 5: - 3D view of Mixing chamber and injector design

Combustion and converging Chamber: -

We use a traditional design of a combustion chamber followed by a converging design here this converging design help to maintain the flow speed between Mach 1 to Mach 1.2 because, at the supersonic speed, it reduces the flow speed and at the subsonic speed, it will increase the flow speed and gives us a best operating range of flow at the end of chamber or to say before staring of the nozzle.

Fig-6: - Schematic representation of combustion chamber

2 Diffuser placed after 4cm at both sides left and right which will use to sort the problem of airflow in the combustion chamber.For continuing flame holding we are using an electric discharger or to say spark points and for this one electronic circuit is placed below the combustion chamber which hasa dimension of 8 cm(height)*12 cm(width)*6 cm(length) and for the diffusion of spark we connect ground with our combustion body which is made by tungsten which is a good conductor of electricity and rests for flame holding will be done by high temperature entering from mixing chamber to combustion chamber.

Fig.7: - 3D view of combustion chamber

Fuel Tank Capacity: -

We are going to use 2 fuel tanks upper side and the downside. The upper side fuel tank will be located above the mixing, combustion, and nozzle and it has dimensions as follows: -

3 cm(height)*16 cm(width)*60 cm(length) and 2 cm(height)*16 cm(width)*30 cm(length) = 3.84L

And downside tank will be located below the mixing chamber with dimensions of 8 cm(height)* 16 cm (width)* 14.1 (length) = 1,8 L,

The total tank capacity is 5.64L which can carry 4.63 Kgof Kerosene bubbled with H2 fuel.

Fig.8: - Both fuel tank 3D representation

Even after taking the upper and down tanks, there are a few places got vacant which are used to placealgorithm -based electric fuel injector pumps which will control the flow of fuel injection mass in the mixing chamber.

Exit Diverging Nozzle: -

SUBSTITUTE SHEET (RULE 26) For the nozzle we use a traditional design of exit nozzles which is horn type diverging design inlet of the nozzle is a square design with a dimension of 6.28 cm(width) * 2 Cm (height) and using 64 polygon count turn square to circular shape which have a diameter of 16 cm and total length of nozzle is 40 cm. This gives us a standard area ratio of 6,01 and also a working range of nozzle is Mach 3 to 4.

Fig.9: - Schematic representation of nozzle

One Diffuser was placed after 20 cm Length for solving the problem of air stuck due to high velocity and temperature from combustion to the nozzle.

Fig.10: - 3D view of nozzle

The Thrust and Force will be: -

Thrust At point C (Starting of Nozzle / from the combustion) The = (Pc*Ac) +(m,in*Vc);

Thrust At point D (Ending of Nozzle) Thd = (Pd*Ad) +(m.out*Vd);

Efficient ThrustE.T, = Thd - The;

Force At point D (Ending of Nozzle) F = Thd - D;

Efficient ForceE F. = E.t. - D;

Compressible flow calculations at different Altitudes (Range Mach 3 to 5): -

Altitude = 5 Km

Inlet Calculations at different shocks dues to different slops: -

SUBSTITUTE SHEET (RULE 26)

Mixing and Combustion Chamber Calculations: -

The efficiency of both mixing and combustion is 0.9

Fig.ll: - Mass flow rates and ratio at Alt = 5 Km

SUBSTITUTE SHEET (RULE 26) Exit Nozzle Calculations: -

Nozzle Efficiency is 0.97 and Ad/Ac - 6.01

Final Thrust, Drag, and Force: -

Fig.12: - Thrust, Drag and Force comparison at Alt = 5 Km

Altitude = 10 Km

Inlet Calculations at different shocks dues to different slops: -

SUBSTITUTE SHEET (RULE 26) Second Shock at angle 10

Mixing and Combustion Chamber Calculations: -

The efficiency of both mixing and combustion is 0.9

Fig.13: - Mass flow rates and ratio at Alt = 10 Km

Exit Nozzle Calculations: -

Nozzle Efficiency is 0.97 and Ad/Ac = 6.01

SUBSTITUTE SHEET (RULE 26)

Final Thrust, Drag, and Force: -

Final Thrust and Force calculations

Fig.14: - Thrust, Drag and Force comparison at Alt = 10 Km

Altitude = 15 Km

Inlet Calculations at different shocks dues to different slops: -

Second Shock at angle 10

SUBSTITUTE SHEET (RULE 26)

Mixing and Combustion Chamber Calculations: -

The efficiency of both mixing and combustion is 0.9

Fig.15: - Mass flow rates and ratio at Alt = 15 Km

Exit Nozzle Calculations: -

Nozzle Efficiency is 0.97 and Ad/Ac = 6.01

SUBSTITUTE SHEET (RULE 26)

Final Thrust, Drag, and Force: -

Fig.16: - Thrust, Drag and Force comparison at Alt = 15 Km

COMPARISON: -

Thrust: - Fig.17: - Thrust Comparison

Force: - Fig.18: - Force Comparison

Drag: - Fig.19: - Drag Comparison

Added Fuel Mass Flow: - Fig.20: - Added Fuel Mass Flow Comparison

SUBSTITUTE SHEET (RULE 26)

Claims

Claims: -

1. HyperBoost Engine Straps will provide extra trust and force to existing cruise and air-air missiles, increasing their range of operation and operating speed.

2. HyperBoost Engine design will provide the best solutions from Mach 3 to Mach 5 for air-breathing engines where Ramjet and Scramjet engines have disadvantages.

3. HyperBoost Engine design can be used as a cruise missile basic design which can travel till Mach 5 which is hypersonic speed.

4. HyperBoost Engine design can be used for rockets that are used for space explorations because this can give them extra trust and force which can increase speed and reduce the cost of space explorations.

5. Here in the mixing chamber, we used a unique design for injectors which is helpful to mix fuel at supersonic flow speed which can be furtherly used in Scramjets and also can use to make new designs and operations of Scramjets which will give us better handling at hypersonic flights.