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US2931170A - Jet reaction and return flow propulsion means - Google Patents

Jet reaction and return flow propulsion means Download PDF

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Publication number
US2931170A
US2931170A US594160A US59416056A US2931170A US 2931170 A US2931170 A US 2931170A US 594160 A US594160 A US 594160A US 59416056 A US59416056 A US 59416056A US 2931170 A US2931170 A US 2931170A
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flow
turbine
return
return flow
annular
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US594160A
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Georg S Mittelstaedt
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    • 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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/90—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
    • F01D1/20—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially axially
    • 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
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles

Definitions

  • This invention- relates to engines, including reaction engines, and-including jet and turbojet systems. be used as a propulsion means for aircraft, marine vessels, vehicles, or other movable objects. It also relates to. propulsion in part by reaction of a jet.
  • the invention relates particularly to the return or reverse flow, which I discovered to be associated with an annularly' discharged fluid stream cooperating with a centerplate, which may have any shape, character or form.
  • return flow or reverse flow is. also meant forward flow and centripetal flow;
  • fannular is alsomeant any encircling outline orfigure.
  • 1By centerplate is also meant any central body, central portion, or any central covering or dividing means.
  • Another object of this invention is to create a simple and practicable. form of auxiliary propulsion means in cooperation with the annularly discharged exhaust stream of a jet reaction device.
  • Another object is to gain motion by utilizing the above mentioned return flow'efi'ct.
  • Another object is to utilize said return flow efiect to drivea turbine or other device.
  • Figure 1 shows a rocket type reaction engine, illustrating the application of the invention.
  • Figure 2 shows a turbojet type reaction engine with an inner turbine and a return-flow operated outer turbine, illustrating the application of the invention.
  • Figure 1 shows a rocket type reaction engine, where the numeral 1 indicates the case and 2 the propellant.
  • the numeral 3 indicates an annular exhaust nozzle, 4 a centerplate, 6 shows a return-flow actuated body, and 5 shows a connecting member between centerplate 4 and body6.
  • the arrows indicate the character and approximate directions of the flow.
  • A indicates the annular flow
  • B the converged or full flow
  • C indicates the return flow which I utilize in this invention to gain motion.
  • Figure 3 shows a.-turbojet type reaction engine, where the numeral 1 indicates the case, 7 the compressor, 8 the combustionchamber. or flame tubes, 3 indicates the annular exhaust nozzle, 4 a centerplate, and 10 a return-flow operated turbine, shown mounted onthe sameshaft 11 with compressor 7. "The arrows indicate the character and approximate directions of the-flow. A indicates the annular flow, B the converged or full flow, and C indicates the return flow which I utilize in this invention to gain motion.
  • Said bodyf6 is situated rearward of the centerplate4 andiiwithin the return flow region C, said body 6 being preferably smaller in' diameter .thansaidcenterplate 4.
  • -..,It is evident that the body 6 is located away from the fluid stream. portions-A-and B. It is also evident that;said body 6 is located'inthe path of the described reverse flow C, said reverseflow C impinging on said body 6, thereby creating motiom :
  • the target surface for said return flow C may be part of the centerplate or engine structure, and said centerplate may be part of the engine structure.”
  • a jetreaction and return flow propulsion device including a combustion chamber, an annular nozzle, and a centerpiece encircled by said annular nozzle, said nozzle leading the exhaust from said combustion chamber to atmosphere; said nozzle discharging an annular fluid stream, said annular'fiuid stream converging and creating a return flow in cooperation with said centerpiece, a turbine situated rearward of said centerpiece and in the path of said return flow, said return fiow exerting a pressure on said turbine, thereby creating motion and rotation.
  • said return-flow turbine having the: same shaft with said compressor.
  • a combustion chamber an. annular nozzle,- and a central part encircled by'said annular nozzle, said nozzle leading the exhaust from said combustion chamber to atmosphere, said nozzle discharging an annular exhaust stream, said annular exhaust stream expanding inward to a full stream and creating a return fiow in cooperation with said central part, a means to utilize said return flow to gain motion, said means comprising a target situated in the path of said return flow, said return flow exerting pressure on said target, tending to move said target.
  • said target comprising a body situated in the path of said return flow, said return flow exerting pressure on said body, tending to move said body forward.
  • said target com prising a body rearward of said central part and separated with a space therefrom, a support for said body, said body being smaller in diameter than said central part.
  • said target comprising a turbine situated in the path of said return flow, said return flow impinging on said turbine, thereby creating rotation.
  • a propulsion device including a means to produce a fiow, an annular nozzle to discharge said flow annularly, a centerplate encircled by said annular nozzle, and a body rearward of said centerplate and separated with a space therefrom, a support for said body, said body being smaller in diameter than said centerplate, the annular flow expanding inward after discharge from said annular nozzle and creating a return flow in cooperation with said centerplate, said return flow exerting pressure on said body, tending to move said body.
  • a system according to claim 16 said body being vaned and rotatably mounted.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Turbines (AREA)

Description

April 5, 1960 G. s. MITTELSTAEDT 2,931,170
JET REACTION AND RETURN 11.0w PROPULSION MEANS Filed June 27, 1956 I 2 3 A i C B I I I I l l l l I I I I I I l I I I l l l l l I I llllll4 V F G 3 INVENTOR JET REACTION AND RETURN FLOW PROPULSION MEANS Georg S. Mittelstaedt, Brooklyn, Application June 27, 1956, Serial No. 594,160 17 Claims. (Cl. 6035.6)
V This invention-:relates to engines, including reaction engines, and-including jet and turbojet systems. be used as a propulsion means for aircraft, marine vessels, vehicles, or other movable objects. It also relates to. propulsion in part by reaction of a jet.
The invention relates particularly to the return or reverse flow, which I discovered to be associated with an annularly' discharged fluid stream cooperating with a centerplate, which may have any shape, character or form. In the text and claims: By return flow or reverse flow is. also meant forward flow and centripetal flow; By fannular is alsomeant any encircling outline orfigure. 1By centerplate is also meant any central body, central portion, or any central covering or dividing means. Y
An object of this invention is to improve reaction engines.
Another object of this invention is to create a simple and practicable. form of auxiliary propulsion means in cooperation with the annularly discharged exhaust stream of a jet reaction device. I i
. Another object is to gain motion by utilizing the above mentioned return flow'efi'ct.
Another object is to utilize said return flow efiect to drivea turbine or other device.
7 Still another object is to provide cooling and ease and simplicity of installatioh V These and other objects will become apparent in the description below, in which characters of reference refer to like-named parts in the drawing.
The drawing shows sectional views of various devices, illustrating the application of the invention, but the invention is not limited to the particular devices illustrated.
Figure 1 shows a rocket type reaction engine, illustrating the application of the invention.
Figure 2 shows a turbojet type reaction engine with an inner turbine and a return-flow operated outer turbine, illustrating the application of the invention.
Figure 3 shows a turbojet type reaction engine having a return-flow operated turbine, illustrating the application of the invention.
Referring in detail to the drawing, Figure 1 shows a rocket type reaction engine, where the numeral 1 indicates the case and 2 the propellant. The numeral 3 indicates an annular exhaust nozzle, 4 a centerplate, 6 shows a return-flow actuated body, and 5 shows a connecting member between centerplate 4 and body6. The arrows indicate the character and approximate directions of the flow. A indicates the annular flow, B the converged or full flow, and C indicates the return flow which I utilize in this invention to gain motion.
Figure 2 shows a turbojet type reaction engine, where the numeral 1 indicates the case, 7 the compressor, 8 the combustion chamber or flame tubes, and 9 the inner turbine. nozzle, 4 a centerplate and 10 a return-flow operated turbine, shown mounted on the same shaft 11 with the compressor 7. The arrows indicate the character and The numeral 3 indicates the annular exhaust,
nited States Patent It may ICC .5" 2 I approximate directions of the flow. A indicates the annular flow, B the converged or full flow, and C indicates the return flow which I utilize in this invention to gain motion.
Figure 3 shows a.-turbojet type reaction engine, where the numeral 1 indicates the case, 7 the compressor, 8 the combustionchamber. or flame tubes, 3 indicates the annular exhaust nozzle, 4 a centerplate, and 10 a return-flow operated turbine, shown mounted onthe sameshaft 11 with compressor 7. "The arrows indicate the character and approximate directions of the-flow. A indicates the annular flow, B the converged or full flow, and C indicates the return flow which I utilize in this invention to gain motion.
The annular flow A converges to a full flow B; and in association with centerplate 4 a return flow. C is created. I have conducted numerous experiments and I have found that theabove defined reverse flow C develops essentially as illustrated and described. I believe that the converging annular fluid stream creates a near vacuum or low pressure pocket at C, andan exterior medium, such as part of the fluid stream is forced into said pocket, thereby creating the reverse flow C.
I propose-to utilize the described reverse flow C to impinge on a targetsuriace or body 6, which may have any suitable shape, character or form. Said bodyf6 is situated rearward of the centerplate4 andiiwithin the return flow region C, said body 6 being preferably smaller in' diameter .thansaidcenterplate 4. -..,It is evident that the body 6 is located away from the fluid stream. portions-A-and B. It is also evident that;said body 6 is located'inthe path of the described reverse flow C, said reverseflow C impinging on said body 6, thereby creating motiom :The target surface for said return flow C may be part of the centerplate or engine structure, and said centerplate may be part of the engine structure."
the turbine 10 which is located rearward, of the center-' Such abody-6 may bevaned and have the characteristics of'a;turbine, and the invention embraces the use of a turbine or related device in cooperation with the defined reversefiow C. A In this'application of the invention the described return flow C is used to furnish power to operate plate 4 and within the return flow region C, said turbine 10 being preferably smaller in diameter than said centerplate 4. The turbine 10 may drive a compressor 7 for furnishing an airstream or other form of compressed air, which may be used in the engine. It is evident that the turbine 10 is located away from the fluid stream portions A and B. It is also evident that said turbine 10 is located in the path of the described reverse flow C, said reverse flow C impinging on said turbine 10, thereby creating rotation and motion.
The described turbine may be attached to any suitable part of the structure. The turbine 10 may be coaxial with the compressor 7, and may be mounted on the same shaft 11 with the compressor 7.
It is part of this invention to utilize this described reverse flow to secure a cooling eflect on the turbine or in the propulsion system.
It is to be noted that changes in form and construction may be made without departing from the spirit or scope of the invention.
I claim:
1. A jet reaction and return flow propulsion device, including a combustion chamber, an annular nozzle for leading the exhaust from said combustion chamber to atmosphere, and a centerplate encircled by said annular nozzle, said nozzle discharging an annular fluid stream, said annular fluid stream converging to a full stream and creating a return flow in cooperation with said centerplate, the return flow region lying within the confines of the annular and converging portion of said fluid stream 4..A system according to claim 2, an inner turbine located upstream of the terminal of the exhaust nozzle, said return-flow turbine being connected with said inner turbine.
5. A system according to claim 4, said return-flow turbine having the same shaft with said inner turbine and with said. compressor.
.6. A jetreaction and return flow propulsion device, including a combustion chamber, an annular nozzle, and a centerpiece encircled by said annular nozzle, said nozzle leading the exhaust from said combustion chamber to atmosphere; said nozzle discharging an annular fluid stream, said annular'fiuid stream converging and creating a return flow in cooperation with said centerpiece, a turbine situated rearward of said centerpiece and in the path of said return flow, said return fiow exerting a pressure on said turbine, thereby creating motion and rotation.
7. A system accordingto claim 6, a compressor for furnishing an airstream for use in the combustion chamber, said return-flow turbine being connected with said compressor.-
8. Ajsystem according to claim 7, said return-flow turbine having the: same shaft with said compressor.
9. .A system according to claim 7, an inner turbine located between the nozzle terminal and the combustion chamber, said return-flow turbine being connected with said inner turbine 10.. A'system according to claim 9, said return-flow turbine having the same shaft with said inner turbine and with said compressor.
- 1'1. In a device of the-class; described, a combustion chamber, an. annular nozzle,- and a central part encircled by'said annular nozzle, said nozzle leading the exhaust from said combustion chamber to atmosphere, said nozzle discharging an annular exhaust stream, said annular exhaust stream expanding inward to a full stream and creating a return fiow in cooperation with said central part, a means to utilize said return flow to gain motion, said means comprising a target situated in the path of said return flow, said return flow exerting pressure on said target, tending to move said target.
12. A system according to claim 11, said target comprising a body situated in the path of said return flow, said return flow exerting pressure on said body, tending to move said body forward.
13. A system according to claim 11, said target com prising a body rearward of said central part and separated with a space therefrom, a support for said body, said body being smaller in diameter than said central part.
14. A system according to claim 11, said target comprising a turbine situated in the path of said return flow, said return flow impinging on said turbine, thereby creating rotation.
' 15. A system according to claim 11, said central part having a fiat end-surface parallel with the nozzle opening.
16. A propulsion device, including a means to produce a fiow, an annular nozzle to discharge said flow annularly, a centerplate encircled by said annular nozzle, and a body rearward of said centerplate and separated with a space therefrom, a support for said body, said body being smaller in diameter than said centerplate, the annular flow expanding inward after discharge from said annular nozzle and creating a return flow in cooperation with said centerplate, said return flow exerting pressure on said body, tending to move said body.
17. A system according to claim 16, said body being vaned and rotatably mounted.
References Cited in the file of this patent UNITED STATES PATENTS 2,256,198 Hahn Sept. 16, 1941 2,489,953 Burney Nov. 29, 1949 2,601,311 McCormick June 24, 1952 OTHER REFERENCES The Rocket Combustion Motor by Dr. Sanger, printed in Astronauticsfor October 1936, pages 4 and 5. Principles of Aerodynamics (Dwinnell), published by McGraw-Hill', 1949, page 166.
US594160A 1956-06-27 1956-06-27 Jet reaction and return flow propulsion means Expired - Lifetime US2931170A (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3012400A (en) * 1960-05-23 1961-12-12 Jr Blake W Corson Nozzle
US3049876A (en) * 1960-03-30 1962-08-21 James F Connors Annular rocket motor and nozzle configuration
US3133410A (en) * 1960-08-15 1964-05-19 Phillips Petroleum Co Burning rate control of solid propellants
US3140583A (en) * 1961-07-21 1964-07-14 United Aircraft Corp Vectoring system for multiple rocket nozzle configuration

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2256198A (en) * 1938-05-27 1941-09-16 Ernst Heinkel Aircraft power plant
US2489953A (en) * 1940-09-04 1949-11-29 Burney Charles Dennistoun Projectile operating with rocket propulsion
US2601311A (en) * 1946-07-22 1952-06-24 Clarence J Mccormick Jet propulsion engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2256198A (en) * 1938-05-27 1941-09-16 Ernst Heinkel Aircraft power plant
US2489953A (en) * 1940-09-04 1949-11-29 Burney Charles Dennistoun Projectile operating with rocket propulsion
US2601311A (en) * 1946-07-22 1952-06-24 Clarence J Mccormick Jet propulsion engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3049876A (en) * 1960-03-30 1962-08-21 James F Connors Annular rocket motor and nozzle configuration
US3012400A (en) * 1960-05-23 1961-12-12 Jr Blake W Corson Nozzle
US3133410A (en) * 1960-08-15 1964-05-19 Phillips Petroleum Co Burning rate control of solid propellants
US3140583A (en) * 1961-07-21 1964-07-14 United Aircraft Corp Vectoring system for multiple rocket nozzle configuration

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