GB2607638A - Propulsion for aerospace applications - Google Patents

Propulsion for aerospace applications Download PDF

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Publication number
GB2607638A
GB2607638A GB2108633.5A GB202108633A GB2607638A GB 2607638 A GB2607638 A GB 2607638A GB 202108633 A GB202108633 A GB 202108633A GB 2607638 A GB2607638 A GB 2607638A
Authority
GB
United Kingdom
Prior art keywords
hypersonic
gas turbine
ramjet
propulsion
reduced
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
GB2108633.5A
Other versions
GB202108633D0 (en
Inventor
Desmond Stephen Lewis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of GB202108633D0 publication Critical patent/GB202108633D0/en
Publication of GB2607638A publication Critical patent/GB2607638A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/401—Liquid propellant rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/02—Plural gas-turbine plants having a common power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/78—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/14—Space shuttles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/80—Application in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Remote Sensing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

Multiple systems of propulsion are used singly or in combination to provide propulsion for aircraft and spacecraft. The types of propulsion may be a hypersonic ramjet/scramjet 1, a fuel tank precooler 2, a vortex tube precooler 3, a reduced weight gas turbine 4, a reduced velocity ramjet 5, a reduced velocity ramjet with gas turbine 6, an increased scalability expander cycle rocket engine 7, an increased power pressure fed rocket engine 8 and a hypersonic gas turbine 9.

Description

Propulsion for aerospace applications This invention relates to propulsive systems for aerospace applications especially for single stage to orbit vehicles.
Various methods of propelling aircraft have been devised for the purposes of reaching orbit in a single stage to orbit vehicle such as a spaceplane. Various methods may prove successful, however, some may prove to be too expensive for commercial use, or too dangerous or unreliable, while some may be considered only worth reserving for emergency use such as for transporting emergency medical supplies or emergency disaster relief supplies. Some may be preferred for only space travel issues such as rescue and recovery or other space issues such as asteroid or comet collisions and space junk and debris collection. Some may be considered too noisy and some may cause environmental issues which may require a periodic change of fuel or propulsion system to keep things in balance with various ecosystems. To overcome this, the present invention proposes a plurality of singular and/or combined propulsion systems, said systems comprising; at least one hypersonic ram/scramjet and/or at least one fuel tank pre-cooler, and/or at least one vortex tube pre-cooler, and/or at least one reduced weight gas turbine, and/or at least one reduced velocity ramjet, and/or at least one reduced velocity ramjet with gas turbine, and/or at least one increased scalability expander cycle rocket engine, and/or at least one increased power pressure fed rocket engine, and/or at least one hypersonic gas turbine.
All of the propulsion systems can be used in multiple different combinations to enable aerospace needs to be catered for with a greatly reduced probability that any one system isn't suitable due to other combinations being available.
Preferably, there are two or more said hypersonic ram/scramjets and/or fuel tank pre-coolers, and/or vortex tube pre-coolers, and/or reduced weight gas turbines, and/or reduced velocity ramjets, and/or reduced velocity ramjets with gas turbines, and/or increased scalability expander cycle rocket engines, and/or increased power pressure fed rocket engines, and/or hypersonic gas turbines.
An example of the invention will now be described by referring to the accompanying drawings: - figures 1,3,5,7,8 and 9 show side views of the propulsion for aerospace applications and; - figures 2,4, and 6 show end views of the propulsion for aerospace applications according to the invention.
Multiple systems for aircraft and spaceplane propulsion are used singularly or combined to provide propulsion, which there may be more than one of, which include a hypersonic ram/scramjet 1, a fuel tank pre-cooler 2, a vortex tube pre-cooler 3, a reduced weight gas turbine 4, a reduced velocity ramjet 5, a reduced velocity ramjet with gas turbine 6, an increased scalability expander cycle rocket engine 7, an increased power pressure fed rocket engine 8, and a hypersonic gas turbine 9.
The potential number of different combinations = 2"-In where n -the number of different propulsion parts = 29 -19 = 503.
represents the number of different combinations and n is subtracted from this because each invention cannot operate on its own for a single stage to orbit vehicle.
This is a very approximate figure, increasing n by 1 gives 1,014, or reducing n by one gives 248.
A hypersonic ram/scramjet 1, is as described in patent number: G82498005; a fuel tank pre-cooler 2, is as described in patent number: GB2522080; a vortex tube pre-cooler 3, is as described in patent number: GB2535811; a reduced weight gas turbine 4, is as described in patent application number: GB1914504.4; a reduced velocity ramjet 5, and a reduced velocity ramjet with gas turbine 6, are described in patent application number: G82010543.3; an increased scalability expander cycle rocket engine 7, is as described in patent number: GB2577133; an increased power pressure fed rocket engine 8, is as described in patent application number-GB2010542.5; and a hypersonic gas turbine 9, is as described in patent application number-GB1915253.7 The optimum combined cycle providing the most power and least drag and least weight may, depending on actual realised performance, be a combination of fuel tank pre-cooling, vortex pre-cooler applied to the reduced velocity ramjet and the hypersonic gas turbine and the increased power pressure fed rocket engine applied to the hypersonic gas turbine.
The reduced velocity ramjet would operate as a turbofan, then ramjet (if required), then turboshaft to power the hypersonic gas turbine.
Figures 1 and 2 show a hypersonic gas turbine at the core of the propulsion system with vortex and fuel tank pre-cooling.
Figures 3 and 4 show a hypersonic ram/scramjet at the core, again with vortex and fuel tank pre-cooling.
Figures 5 and 6 show a shared propulsion system with both a hypersonic gas turbine and a hypersonic ram/scramjet also with vortex and fuel tank pre-cooling.
Figure 7 shows a shared propulsion system with both a hypersonic gas turbine and a hypersonic ramjet also with vortex and fuel tank pre-cooling which includes an extra central electrical generator of the hypersonic ram/scramjet which allows slightly smaller electrical generators to achieve greater rotational speeds due to the smaller centrifugal loads on the rotors which increases the power to weight ratio of the electrical generators.
Figure 8 shows a shared propulsion system with both a hypersonic gas turbine and a hypersonic ram/scramjet also with vortex and fuel tank pre-cooling which shows a single larger central electrical generator of the hypersonic ram/scramjet which due to its size allows a greater efficiency than smaller electrical generators.
Figure 9 shows a shared propulsion system with both a hypersonic gas turbine and a hypersonic ram/scramjet also with vortex and fuel tank pre-cooling with angled vortex pre-cooling ducts which reduce intake drag, airflow resistance and pressure losses due to the gentler angle changes of the intake flow.

Claims (2)

  1. Claims * 1 A plurality of singular and/or combined propulsion systems, said systems comprising; at least one hypersonic ram/scramjet and/or at least one fuel tank pre-cooler, and/or at least one vortex tube pre-cooler, and/or at least one reduced weight gas turbine, and/or at least one reduCed velocity ramjet, and/or at least one reduced velocity ramjet with gas turbine, and/or at least one increased scalability expander cycle rocket engine, and/or at least one increased power pressure fed rocket engine, and/or at least one hypersonic gas turbine.
  2. 2 A plurality of singular and/or combined propulsion systems according to claim 1, wherein there are two or more said hypersonic ram/scramjets and/or fuel tank pre-coolers, and/or vortex tube pre-coolers, and/or reduced weight gas turbines, and/or reduced velocity ramjets, and/or reduced velocity ramjets with gas turbines, and/or increased scalability expander cycle rocket engines, and/or increased power pressure fed rocket engines, and/or hypersonic gas turbines.
GB2108633.5A 2021-06-09 2021-06-17 Propulsion for aerospace applications Pending GB2607638A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB202108296 2021-06-09

Publications (2)

Publication Number Publication Date
GB202108633D0 GB202108633D0 (en) 2021-08-04
GB2607638A true GB2607638A (en) 2022-12-14

Family

ID=77050674

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2108633.5A Pending GB2607638A (en) 2021-06-09 2021-06-17 Propulsion for aerospace applications

Country Status (1)

Country Link
GB (1) GB2607638A (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012058758A1 (en) * 2010-11-02 2012-05-10 Atantis Research Labs Inc. Multiple mode jet engine
GB2498005A (en) * 2011-12-31 2013-07-03 Stephen Desmond Lewis A Hypersonic Ram/Scramjet

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012058758A1 (en) * 2010-11-02 2012-05-10 Atantis Research Labs Inc. Multiple mode jet engine
GB2498005A (en) * 2011-12-31 2013-07-03 Stephen Desmond Lewis A Hypersonic Ram/Scramjet

Also Published As

Publication number Publication date
GB202108633D0 (en) 2021-08-04

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