US3105355A - Support arrangement - Google Patents

Support arrangement Download PDF

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Publication number
US3105355A
US3105355A US49919A US4991960A US3105355A US 3105355 A US3105355 A US 3105355A US 49919 A US49919 A US 49919A US 4991960 A US4991960 A US 4991960A US 3105355 A US3105355 A US 3105355A
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United States
Prior art keywords
wall part
housing
support
propulsion unit
outwardly disposed
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Expired - Lifetime
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US49919A
Inventor
Werner A Bruder
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Daimler Benz AG
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Daimler Benz AG
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Publication date
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
    • B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F02K7/005—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 the engine comprising a rotor rotating under the actions of jets issuing from this rotor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the construction and arrangement of the securing base or foot portion of jet propulsion units arranged in a freely exposed manner, and more particularly relates to the construction and arrangement of the securing base or foot portion of jet propulsion units, especially of ram jet propulsion plants preferably having an elliptical or quasi elliptical cross-section and arranged along the outwardly disposed ends of the propeller or rotor blades of helicopters.
  • the ram jet propulsion units arranged at the ends of the propeller or rotor blades which consist essentially only of a sheet-metal casing or envelope serving as combustion chamber, and which are provided in the front thereof with a double-walled inlet diffuser and at the rear end thereof with a nozzle-shaped constriction, are subjected during the operation thereof to relatively high centrifugal forces and stresses. Even though the propulsion unit housing or casing is cooled on the outside thereof by the air flowing past the same, the rigidity of the housing or casing nevertheless suffers 'by reason of the relatively high temperatures prevailing at the inside thereof. Additionally, the propulsion unit housing is normally constructed of relatively thin walls for reasons of weight-saving.
  • the problem with which the present invention is concerned consists in so constructing the supporting base or foot portion of the propulsion unit, preferably of one having an elliptical or quasi elliptical cross-section in such a manner that not only high rigidity properties are attained but also favorable conditions are created as regards cooling of the sector of the housing facing the support arrangement or facing the propeller or rotor blade end.
  • Another object of the present invention resides in the provision of a support arrangement for a jet propulsion unit of the type described hereinabove which is of relative light weight and provides adequate cooling not only of the outer housing walls but also of the inner walls of the combustion chamber facing the supporting base.
  • a still further object of the present invention resides in the provision of a light weight housing for jet propulsion units which minimizes the possibility of deformations that may otherwise occur during operation of the unit.
  • a further object of the present invention resides in the provision of a jet propulsion unit housing which'oifers high rigidity characteristics in addition to favorable conditions with respect to cooling of the construction thereof.
  • reference character F generally designates the base or foot portion of the ram jet propulsion unit which itself is generally designated by reference character S.
  • the base F of the jet propulsion unit S is detachably connected or secured, in any known suitable manner, with the propeller or rotor end 11.
  • the sector of the drive unit housing facing the propeller or rotor blade end 11 is constructed as a bearer body generally designated by reference character T and consists essentially of anouter wall part 12 and of an inner wall part 13 which are rigidly connected with each other by means of intermediate profile members 14.
  • the body T has an arcuate extent less than half the arcuate extent of the combustion chamber.
  • the base F further consists of two sheet-metal web plates 15 and 16 extending in the direction of the longitudinal axis of the propulsion or drive unit which are reinforced with each other by means of transverse web portions 17.
  • the center sections 15' and 16 of the two sheet-metal web plates 15 and 16 are rigidly connected each with the ends 12' and 12", respectively, of the outer wall parts 12, and thereby constitute in effect a continuation of the latter.
  • the ends '15" and 16" of the sheetmetal web plates 15 and 16, the ends 13' and 13 of the inner wall parts '13 and the ends 18 and 18" of the housing sector 18 opposite the support base F form a common securing or fastening joint and are connected with each other in any suitable manner, for example, by welding.
  • Holder or support members 19 are rigidly inserted into the inner wall part 13 for purposes of supporting thereon a central flame holder 20.
  • the bearer body T is open in the front and in the rear thereof so that the air can flow freely through the channels 21 to thereby cool the walls thereof.
  • the support or bearer body member T is locally interrupted for purposes of extending therethrough a spark plug 23, and an insert body member 22 for the spark plug 23 is rigidly secured, for example by welding, in this local interruption.
  • a base construction for the support of a freely exposed propulsion unit especially of a propulsion unit arranged at the outwardly disposed end of a propeller blade of a helicopter, comprising housing means forming a combustion chamber and including a plurality of housing sectors, support means for supporting said housing means on said outwardly disposed end, one of said factors facing said support means and comprising wall parts including an outer wall part and an inner wall part defining a space therebetween for the flow of air, means for rigidly reinforcing said wall parts and for providing channels for said flow of air comprising profile members connecting said outer wall part and said inner wall part, said support means comprising web plate means secured to said outwardly disposed propeller end, said outer wall part being of less arcuate extent than said inner wall part, said Web plate means engaging the ends of said outer wall part and comprising plate portions extending past said outer Wall part ends into further engagement with said housing means.

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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)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Ignition Installations For Internal Combustion Engines (AREA)

Description

Oct. 1, 1963 w. A. BRUDER SUPPORT ARRANGEMENT Filed Aug. 16. 1960 INVENTOR WERNER A. BRUDER BY 0 f ATTORNEYS United States Patent 3,195,355 SUPPORT ARRANGEMENT Werner A. Brazier, Stuttgart-Sehonberg, Germany, as-
signor to Daimler-Benz Aktiengeselischaft, Stuttgart- Unterturklieirn, Germany Filed Aug. 16, 1960, Ser. No. 49,919 Claims priority, application Germany Aug. 28, 1959 (Cl. Gil-39.31)
The present invention relates to the construction and arrangement of the securing base or foot portion of jet propulsion units arranged in a freely exposed manner, and more particularly relates to the construction and arrangement of the securing base or foot portion of jet propulsion units, especially of ram jet propulsion plants preferably having an elliptical or quasi elliptical cross-section and arranged along the outwardly disposed ends of the propeller or rotor blades of helicopters.
The ram jet propulsion units arranged at the ends of the propeller or rotor blades which consist essentially only of a sheet-metal casing or envelope serving as combustion chamber, and which are provided in the front thereof with a double-walled inlet diffuser and at the rear end thereof with a nozzle-shaped constriction, are subjected during the operation thereof to relatively high centrifugal forces and stresses. Even though the propulsion unit housing or casing is cooled on the outside thereof by the air flowing past the same, the rigidity of the housing or casing nevertheless suffers 'by reason of the relatively high temperatures prevailing at the inside thereof. Additionally, the propulsion unit housing is normally constructed of relatively thin walls for reasons of weight-saving.
It is already known in the prior art to construct the housing of ram jet propulsion units arranged at the ends of the propeller or rotor blades of elliptically-shaped or quasi-elliptical cross-section in order to maintain as small as possible the deformation of the housing during operation.
The problem with which the present invention is concerned consists in so constructing the supporting base or foot portion of the propulsion unit, preferably of one having an elliptical or quasi elliptical cross-section in such a manner that not only high rigidity properties are attained but also favorable conditions are created as regards cooling of the sector of the housing facing the support arrangement or facing the propeller or rotor blade end.
It is proposed as solution to the problem in accordance with the present invention to construct the aforementioned housing sector as a double-walled support body which is open to the air flow.
According to another feature of the present invention, it is proposed to rigidly connect with each other the inner and outer wall parts of the housing sector by means of intermediate profile members which form simultaneously flow channel air passages so that a bearer member of lattice or trussing-type framework results therefrom.
Accordingly, it is an object of the present invention to provide a support base for a jet propulsion unit, especially for a ram jet propulsion unit arranged at the outer ends of the propeller or rotor blades in helicopters which obviates the disadvantages and shortcomings of the prior art construction.
It is another object of the present invention to provide a support base and housing construction for a jet propulsion unit of the type described hereinabove in which the forces and resulting stresses, especially the centrifugal forces and stresses resulting therefrom, can be readily absorbed notwithstanding the light-weight properties of the housing.
Another object of the present invention resides in the provision of a support arrangement for a jet propulsion unit of the type described hereinabove which is of relative light weight and provides adequate cooling not only of the outer housing walls but also of the inner walls of the combustion chamber facing the supporting base.
A still further object of the present invention resides in the provision of a light weight housing for jet propulsion units which minimizes the possibility of deformations that may otherwise occur during operation of the unit.
A further object of the present invention resides in the provision of a jet propulsion unit housing which'oifers high rigidity characteristics in addition to favorable conditions with respect to cooling of the construction thereof.
These and other objects, features and advantages of the present invention will become more obvious from the following description when taken in connection with the accompanying drawing which shows in the single FIG- URE thereof, for purposes of illustration only, one embodiment in accordance with the present invention.
Referring now to the drawing which shows in the single figure thereof a cross-sectional view through a portion of a ram jet propulsion unit with the cross-section thereof taken perpendicularly to the longitudinal axis thereof, reference character F generally designates the base or foot portion of the ram jet propulsion unit which itself is generally designated by reference character S. The base F of the jet propulsion unit S is detachably connected or secured, in any known suitable manner, with the propeller or rotor end 11. The sector of the drive unit housing facing the propeller or rotor blade end 11 is constructed as a bearer body generally designated by reference character T and consists essentially of anouter wall part 12 and of an inner wall part 13 which are rigidly connected with each other by means of intermediate profile members 14. As indicated in the single figure of the drawing, the body T has an arcuate extent less than half the arcuate extent of the combustion chamber.
The base F further consists of two sheet- metal web plates 15 and 16 extending in the direction of the longitudinal axis of the propulsion or drive unit which are reinforced with each other by means of transverse web portions 17. The center sections 15' and 16 of the two sheet- metal web plates 15 and 16 are rigidly connected each with the ends 12' and 12", respectively, of the outer wall parts 12, and thereby constitute in effect a continuation of the latter. The ends '15" and 16" of the sheetmetal web plates 15 and 16, the ends 13' and 13 of the inner wall parts '13 and the ends 18 and 18" of the housing sector 18 opposite the support base F form a common securing or fastening joint and are connected with each other in any suitable manner, for example, by welding.
Holder or support members 19 are rigidly inserted into the inner wall part 13 for purposes of supporting thereon a central flame holder 20.
The bearer body T is open in the front and in the rear thereof so that the air can flow freely through the channels 21 to thereby cool the walls thereof.
According to the embodiment illustrated in the single figure of the drawing, the support or bearer body member T is locally interrupted for purposes of extending therethrough a spark plug 23, and an insert body member 22 for the spark plug 23 is rigidly secured, for example by welding, in this local interruption.
While I have shown and described one embodiment in accordance with the present invention, it is understood that the same is not limited thereto but is susceptible of many changes and modifications within the spirit and scope of the present invention, and I, therefore, do not wish to be limited to the details shown and described herein, 'but intend to cover all such changes and modifications as are encompassed by the scope of the appended claims.
I claim:
1. A base construction for the support of a freely exposed propulsion unit, especially of a propulsion unit arranged at the outwardly disposed end of a propeller blade of a helicopter, comprising housing means forming a combustion chamber and including a plurality of housing sectors, support means for supporting said housing means on said outwardly disposed end, one of said factors facing said support means and comprising wall parts including an outer wall part and an inner wall part defining a space therebetween for the flow of air, means for rigidly reinforcing said wall parts and for providing channels for said flow of air comprising profile members connecting said outer wall part and said inner wall part, said support means comprising web plate means secured to said outwardly disposed propeller end, said outer wall part being of less arcuate extent than said inner wall part, said Web plate means engaging the ends of said outer wall part and comprising plate portions extending past said outer Wall part ends into further engagement with said housing means. 2. A base construction for the support of a freely exposed propulsion unit according to claim 1, wherein said inner wall part is provided with support means supporting therein a flame holder.
3. A base construction for the support of a freely exposed propulsion unit according to claim 1, wherein the housing sector opposite said support means is provided with the end portions extending in directions toward said outwardly disposed end of said propeller blade, and wherein said last-mentioned two end portions, the two ends of said inner wall part and the ends of said plate portions are rigidly connected with each other at a common place.
4. A base construction for the support of a freely exposed propulsion unit according to claim 1, wherein 3 the housing sector opposite said support means includes two end portions extending in directions toward said outwardly disposed end of said propeller blade, said two end portions being rigidly connected with said inner wall part and with said web plate means.
5. A base construction for the support of a freely exposed propulsion unit according to claim 1, wherein said plate port-ions define with said inner wall part further spaces for the flow of air.
6. A base construction for the supportof a freely exposed propulsion unit according to claim 5, wherein said profile members comprise portions thereof disposed in said further spaces.
7. A base construction for the support of a freely exposed propulsion unit according to claim 6, wherein said portions of said profile members are in connecting relationship with said inner wall part and said plate portions. 7
References Cited in the file of this patent UNITED STATES PATENTS 2,397,998 Goddard Apr. 9, 1946 2,591,676 Clayton Apr. 8, 1952 2,606,608 Barclay Aug. 5, 1952 2,612,748 Tenney et al. Oct. 7, 1952 2,742,972 Apostolescu Apr. 24, 1956 2862,680 Berger Dec. 2, 1958 2,946,191 Dress Iuly'26, 1960 FOREIGN PATENTS 581,217 Great Britain Oct. 4, 1946 614,621 Great Britain Dec. 12, 1948 715,391 Great Britain Sept. 15, 1954 753,545 Great Britain July 2-5, 1956 8 15,90 1 Great Britain July 1, 1959 534,912 Italy Oct. 28, 1955

Claims (1)

1. A BASE CONSTRUCTION FOR THE SUPPORT OF A FREELY EXPOSED PROPULSION UNIT, ESPECIALLY OF A PROPULSION UNIT ARRANGED AT THE OUTWARDLY DISPOSED END OF A PROPELLER BLADE OF A HELICOPTER, COMPRISING HOUSING MEANS FORMING A COMBUSTION CHAMBER AND INCLUDING A PLURALITY OF HOUSING SECTORS, SUPPORT MEANS FOR SUPPORTING SAID HOUSING MEANS ON SAID OUTWARDLY DISPOSED END, ONE OF SAID FACTORS FACING SAID SUPPORT MEANS AND COMPRISING WALL PARTS INCLUDING AN OUTER WALL PART AND AN INNER WALL PART DEFINING A SPACE THREBETWEEN FOR THE FLOW OF AIR, MEANS FOR RIGIDLY REINFORCING SAID WALL PARTS AND FOR PROVIDING CHANNELS FOR SAID FLOW OF AIR COMPRISING PROFILE MEMBERS CONNECTING SAID OUTER WALL PART AND SAID INNER WALL PART SAID SUPPORT MEANS COMPRISING WEB PLATE MEANS SECURED TO SAID OUTWARDLY DISPOSED PROPELLER END, SAID OUTER WALL PART BEING OF LESS ARCUATE EXTENT THAN SAID INNER WALL PART,
US49919A 1959-08-28 1960-08-16 Support arrangement Expired - Lifetime US3105355A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED31383A DE1105284B (en) 1959-08-28 1959-08-28 Formation of the fastening foot of free-standing jet engines, in particular ramjet engines

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US3105355A true US3105355A (en) 1963-10-01

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3352114A (en) * 1965-07-17 1967-11-14 Rolls Royce Mounting means for separately supporting a gas turbine engine and a jet pipe in an engine pod

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2397998A (en) * 1940-04-15 1946-04-09 Daniel And Florence Guggenheim Propelling apparatus for aircraft
GB581217A (en) * 1944-06-20 1946-10-04 Fairey Aviat Co Ltd Improvements in or relating to power plants for helicopters
GB614621A (en) * 1946-07-25 1948-12-17 Cierva Autogiro Co Ltd Improvements in and relating to rotative aerofoils with propulsive ducts
US2591676A (en) * 1948-12-17 1952-04-08 Jr Harry H Clayton Ejector cooling shroud for use on the exhaust systems of turbojet aircraft engines
US2605608A (en) * 1946-06-27 1952-08-05 Jr Frank D Barclay Jet reaction motor
US2612748A (en) * 1946-04-06 1952-10-07 Tenney Pulse jet mount
GB715391A (en) * 1951-09-13 1954-09-15 Fairey Aviat Co Ltd Improvements relating to helicopters having jet-driven rotors
US2742972A (en) * 1952-05-17 1956-04-24 Apostolescu Stefan Turbo jet helicopter
GB753545A (en) * 1954-01-21 1956-07-25 Saunders Roe Ltd Improvements in or relating to rotor blades for helicopters
US2862680A (en) * 1955-03-17 1958-12-02 Emile Auguste Bourcart Helicopter
GB815901A (en) * 1955-03-04 1959-07-01 Fairey Aviat Co Ltd Improvements relating to jet driven helicopters
US2946191A (en) * 1954-04-12 1960-07-26 Nl I Voor Vliegtuigontwikkelin Ramjet for a rotating member such as a rotor or propeller of an aircraft

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2397998A (en) * 1940-04-15 1946-04-09 Daniel And Florence Guggenheim Propelling apparatus for aircraft
GB581217A (en) * 1944-06-20 1946-10-04 Fairey Aviat Co Ltd Improvements in or relating to power plants for helicopters
US2612748A (en) * 1946-04-06 1952-10-07 Tenney Pulse jet mount
US2605608A (en) * 1946-06-27 1952-08-05 Jr Frank D Barclay Jet reaction motor
GB614621A (en) * 1946-07-25 1948-12-17 Cierva Autogiro Co Ltd Improvements in and relating to rotative aerofoils with propulsive ducts
US2591676A (en) * 1948-12-17 1952-04-08 Jr Harry H Clayton Ejector cooling shroud for use on the exhaust systems of turbojet aircraft engines
GB715391A (en) * 1951-09-13 1954-09-15 Fairey Aviat Co Ltd Improvements relating to helicopters having jet-driven rotors
US2742972A (en) * 1952-05-17 1956-04-24 Apostolescu Stefan Turbo jet helicopter
GB753545A (en) * 1954-01-21 1956-07-25 Saunders Roe Ltd Improvements in or relating to rotor blades for helicopters
US2946191A (en) * 1954-04-12 1960-07-26 Nl I Voor Vliegtuigontwikkelin Ramjet for a rotating member such as a rotor or propeller of an aircraft
GB815901A (en) * 1955-03-04 1959-07-01 Fairey Aviat Co Ltd Improvements relating to jet driven helicopters
US2862680A (en) * 1955-03-17 1958-12-02 Emile Auguste Bourcart Helicopter

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3352114A (en) * 1965-07-17 1967-11-14 Rolls Royce Mounting means for separately supporting a gas turbine engine and a jet pipe in an engine pod

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GB892525A (en) 1962-03-28
DE1105284B (en) 1961-04-20

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