US3879937A - Aerodynamic pressure-wave machine - Google Patents

Aerodynamic pressure-wave machine Download PDF

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Publication number
US3879937A
US3879937A US393818A US39381873A US3879937A US 3879937 A US3879937 A US 3879937A US 393818 A US393818 A US 393818A US 39381873 A US39381873 A US 39381873A US 3879937 A US3879937 A US 3879937A
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United States
Prior art keywords
pressure
rotor
cells
hot gas
compressed
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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.)
Expired - Lifetime
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US393818A
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English (en)
Inventor
Ernst Jenny
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BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F13/00—Pressure exchangers
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/02—Gas-turbine plants characterised by the use of combustion products as the working fluid using exhaust-gas pressure in a pressure exchanger to compress combustion-air
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant

Definitions

  • ABSTRACT An aerodynamic pressure wave machine for effecting an exchange of energy between two gases, a hot gas being expanded from a higher to a lower pressure level and a cold gas being compressed from a lower pressure to a higher pressure, by means of a celled rotor, wherein the rotor cells are inclined with respect to the axis such that opposite ends of the cells lie on different diameters, the hot gas entering and also leaving at the end of the rotor having the greater cell diameter and the cold gas entering and also leaving at the end of the rotor having the smaller cell diameter.
  • This structural arrangement of the rotor cells is particularly advantageous in a case where the pressure of the compressed cold gas and the hot gas to be expanded differ only slightly in the high-pressure zone, whereas the pressure of the expanding hot gas in the low-pressure zone is substantially higher than the pressure of the cold gas to be compressed.
  • the radial height of the cells can be varied between one end of the rotor and the other, and the variation in height can be designed in such manner that the cell cross-section area remains constant over the length of the cells.
  • the present invention concerns an aerodynamic pressure-wave machine the rotor of which, provided with cells, is located between two side portions, one of which incorporates the inlet and exhaust ports for the hot gas while the other incorporates the inlet and exhaust ports for the cold gas, intended for a process in which the pressures of the compressed cold gas and the hot gas to be expanded differ only little in the highpressure zone, whereas the pressure of the expanding hot gas in the low-pressure zone is substantially higher than the pressure of the cold gas to be compressed.
  • a hot gas is expanded from pressure 12 to pressure p and the energy of expansion thus obtained is used to compress a cold gas (termed air in the following, as it is this which is most frequently involved), from pressure p to pressure p
  • a cold gas (termed air in the following, as it is this which is most frequently involved)
  • the indices v and n denote, respectively, before and after passing through the rotor, while 1 and 2 denote the lower and higher pressure levels, respectively.
  • the object of the invention is to create a pressurewave machine which is as simple as possible and with which, in contrast to a machine operating in accordance with the known process, the pressure difference p p can be increased without at the same time having to increase the pressure difference p p
  • This object is achieved in that the cells of the rotor are inclined with respect to the rotor axis such that opposite ends of the cells lie on different diameters the hot gas entering and also leaving at the end of the rotor having the greater cell diameter and the cold gas entering and also leaving at the end of the rotor having the smaller cell diameter.
  • Variations of the pressurewave process are possible by varying the radial height of the cells between one end of the rotor and the other.
  • FIG. 1 shows the rotor of a pressure-wave machine located between a driven machine and a prime mover
  • FIG. 2 shows schematically the evolution of a cylindrical section at half the height of the cells through the rotor and through the adjacent parts of the side portions of the housing;
  • FIG. 3 represents the corresponding wave cycle in the form of a pressure/velocity diagram.
  • FIG. 1 an aerodynamic pressure-wave machine, of which only the rotor 4 is shown, is located between the compressor 1 and the gas turbine 2, which are mounted on a common shaft 3.
  • the rotor 4 can run at the same speed as the turboset or, as indicated by the gap between shaft 3 and rotor 4, it can be driven independently of the gas turbine.
  • the cells 5, which in the example shown are of uniform cross-section over their length, are inclined with respect to the rotor axis such that opposite ends of the cells lie on different diameters of the rotor.
  • the cells are on an average inclined to the rotor axis by an angle a.
  • the cells do not have to lie along an axial section, but can also curve out from the plane of the drawing, which represents such an axial section. It is characteristic, however, that even with the cells designed in such a modified manner the cells, projected cylindrically onto the plane of the drawing, must have an inclination to the rotor axis. With this form of rotor it is possible, by varying the radial cell height, to increase, reduce or maintain constant the cross-section area over the length of the cells.
  • the air is then passed to the combustor 9 and having been heated by combustion flows in the direction of arrow 10 to the rotor 4 as hot, energy-imparting gas, enters the rotor through an inlet port 2v at the end with the larger cell diameter, once again undergoes the pressure-wave process and leaves through an exhaust port In at the same end of the rotor in the direction of arrow 11, whereupon it flows to the gas turbine 2.
  • the inlet and exhaust ports referred to are not, however, shown in FIG. 1).
  • FIG. 2 shows the evolution of a cylindrical section through the rotor of a pressure-wave machine with a very simple wave pattern and four ports, i.e., a distance/time diagram
  • FIG. 3 is the corresponding pressure/velocity diagram as is normally employed with the characteristics method of non-steady gas dynamics.
  • This diagram shows the condition during the course of the gas dynamic process in terms of pressure ratio (p/p H and flow velocity related to the sonic velocity u/a
  • the states at the point of intersection between two characteristics are numbered in sequence from 50 to 55'.
  • the regions in which these states obtain are denoted by the same numbers but omitting the primes
  • the rotor turns in the direction of the arrow U between the two side portions 13 and 14 of the housing.
  • the cells are supplied with fresh air from inlet port lv.
  • a compression wave between regions 55 and 50 retards the flow velocity to zero and thus subjects the contents of the cell to an initial stage of compression. Compression proper begins as soon as a cell opens on the side of inlet port 2v. The compressed air is expelled through exhaust port 2n, the expanded gas through exhaust port In, and fresh air is drawn in through inlet port 1v until state is reached once again.
  • FIG. 3 the changes of state of this process are shown by full lines.
  • the characteristics of state are curved by the influence of centrifugal force.
  • the broken lines indicate the changes of state when the cells of the rotor are axis-parallel in the usual way. It is shown that, in accordance with the set objective, with a rotor having inclined cells in accordance with the invention, the pressure difference p p,-,, is much greater, and at the same time the pressure difference p p is reduced.
  • the improved pressure-wave machine with inclined cells can be used to advantage as a means of charging internal combustion engines if the exhaust back pressure is very high, and also for improving low-pressure scavenging in the pressure-wave machine. It can equally be provided with more than two inlet ports and two exhaust ports per wave cycle, and can also have direction-changing ducts.
  • the cells of said rotor are inclined with respect to the rotor axis such that opposite ends of the cells lie on different diameters, the hot gas entering and also leaving at the end of the rotor having the greater cell diameter and the cold gas entering and also leaving at the end of the rotor having the smaller cell diameter.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
US393818A 1972-10-25 1973-09-04 Aerodynamic pressure-wave machine Expired - Lifetime US3879937A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1552072A CH550937A (de) 1972-10-25 1972-10-25 Aerodynamische druckwellenmaschine.

Publications (1)

Publication Number Publication Date
US3879937A true US3879937A (en) 1975-04-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
US393818A Expired - Lifetime US3879937A (en) 1972-10-25 1973-09-04 Aerodynamic pressure-wave machine

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US (1) US3879937A (US20020128544A1-20020912-P00008.png)
JP (1) JPS5520080B2 (US20020128544A1-20020912-P00008.png)
AT (1) AT324048B (US20020128544A1-20020912-P00008.png)
BE (1) BE806396A (US20020128544A1-20020912-P00008.png)
CA (1) CA995638A (US20020128544A1-20020912-P00008.png)
CH (1) CH550937A (US20020128544A1-20020912-P00008.png)
DK (1) DK141131B (US20020128544A1-20020912-P00008.png)
FR (1) FR2204756B1 (US20020128544A1-20020912-P00008.png)
GB (1) GB1434253A (US20020128544A1-20020912-P00008.png)
IT (1) IT998857B (US20020128544A1-20020912-P00008.png)
NL (1) NL169774C (US20020128544A1-20020912-P00008.png)
SE (1) SE407442B (US20020128544A1-20020912-P00008.png)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4733536A (en) * 1986-10-22 1988-03-29 Gas Research Institute Integrated mechanical vapor recompression apparatus and process for the cogeneration of electric and water-based power having a recirculation control system for part-load capacity
US5052895A (en) * 1989-08-17 1991-10-01 Asea Brown Boveri Ltd. Pressure wave machine
US5916125A (en) * 1997-05-16 1999-06-29 Allison Engine Company, Inc. Forced purge wave rotor
US6449939B1 (en) 2000-05-26 2002-09-17 Rolls-Royce Corporation Pulsed detonation engine wave rotor
US20080000238A1 (en) * 2005-11-09 2008-01-03 Office National D'etudes Et De Recherches Aerospatials (Onera) High efficiency thermal engine
USRE45396E1 (en) 2004-11-12 2015-03-03 Board Of Trustees Of Michigan State University Wave rotor apparatus
US9512805B2 (en) 2013-03-15 2016-12-06 Rolls-Royce North American Technologies, Inc. Continuous detonation combustion engine and system
US9856791B2 (en) 2011-02-25 2018-01-02 Board Of Trustees Of Michigan State University Wave disc engine apparatus
US10393383B2 (en) 2015-03-13 2019-08-27 Rolls-Royce North American Technologies Inc. Variable port assemblies for wave rotors
US10502131B2 (en) 2015-02-20 2019-12-10 Rolls-Royce North American Technologies Inc. Wave rotor with piston assembly
US10641169B2 (en) 2017-06-09 2020-05-05 General Electric Company Hybrid combustor assembly and method of operation
US10969107B2 (en) 2017-09-15 2021-04-06 General Electric Company Turbine engine assembly including a rotating detonation combustor
US11674476B2 (en) 2017-06-09 2023-06-13 General Electric Company Multiple chamber rotating detonation combustor

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3762535D1 (de) * 1986-02-28 1990-06-07 Bbc Brown Boveri & Cie Durch die gaskraefte angetriebener, freilaufender druckwellenlader.
NO168548C (no) * 1989-11-03 1992-03-04 Leif J Hauge Trykkveksler.
CH680680A5 (US20020128544A1-20020912-P00008.png) * 1989-12-06 1992-10-15 Asea Brown Boveri
CN115013154B (zh) * 2022-06-27 2024-06-11 北京航空航天大学宁波创新研究院 一种通道扩张的波转子系统

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2764340A (en) * 1949-09-09 1956-09-25 Jendrassik Developments Ltd Pressure exchangers
US2946184A (en) * 1951-11-08 1960-07-26 Jendrassik Developments Ltd Pressure exchangers and applications thereof
US3003315A (en) * 1955-10-26 1961-10-10 Spalding Dudley Brian Compression ignition pressure exchanger
US3043106A (en) * 1959-09-22 1962-07-10 Jr Richard R Coleman Gas turbine engine
US3209986A (en) * 1961-05-02 1965-10-05 Power Jets Res & Dev Ltd Pressure exchangers
US3374942A (en) * 1965-08-12 1968-03-26 Bbc Brown Boveri & Cie Rotary pressure transformer
US3486686A (en) * 1967-03-30 1969-12-30 Rolls Royce Pressure exchangers

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR877085A (fr) * 1940-12-07 1942-11-26 Brown échangeur de pression
GB843911A (en) * 1955-06-30 1960-08-10 Ronald Denzil Pearson Improvements in pressure exchangers

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2764340A (en) * 1949-09-09 1956-09-25 Jendrassik Developments Ltd Pressure exchangers
US2946184A (en) * 1951-11-08 1960-07-26 Jendrassik Developments Ltd Pressure exchangers and applications thereof
US3003315A (en) * 1955-10-26 1961-10-10 Spalding Dudley Brian Compression ignition pressure exchanger
US3043106A (en) * 1959-09-22 1962-07-10 Jr Richard R Coleman Gas turbine engine
US3209986A (en) * 1961-05-02 1965-10-05 Power Jets Res & Dev Ltd Pressure exchangers
US3374942A (en) * 1965-08-12 1968-03-26 Bbc Brown Boveri & Cie Rotary pressure transformer
US3486686A (en) * 1967-03-30 1969-12-30 Rolls Royce Pressure exchangers

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4733536A (en) * 1986-10-22 1988-03-29 Gas Research Institute Integrated mechanical vapor recompression apparatus and process for the cogeneration of electric and water-based power having a recirculation control system for part-load capacity
US5052895A (en) * 1989-08-17 1991-10-01 Asea Brown Boveri Ltd. Pressure wave machine
US5916125A (en) * 1997-05-16 1999-06-29 Allison Engine Company, Inc. Forced purge wave rotor
US6351934B2 (en) 1997-05-16 2002-03-05 Rolls-Royce Corporation Forced purge wave rotor
US6449939B1 (en) 2000-05-26 2002-09-17 Rolls-Royce Corporation Pulsed detonation engine wave rotor
USRE45396E1 (en) 2004-11-12 2015-03-03 Board Of Trustees Of Michigan State University Wave rotor apparatus
CN100529358C (zh) * 2005-11-09 2009-08-19 奥尼拉(国家宇航研究所) 高效热机
US7610762B2 (en) 2005-11-09 2009-11-03 Onera High efficiency thermal engine
US20080000238A1 (en) * 2005-11-09 2008-01-03 Office National D'etudes Et De Recherches Aerospatials (Onera) High efficiency thermal engine
US9856791B2 (en) 2011-02-25 2018-01-02 Board Of Trustees Of Michigan State University Wave disc engine apparatus
US9512805B2 (en) 2013-03-15 2016-12-06 Rolls-Royce North American Technologies, Inc. Continuous detonation combustion engine and system
US10502131B2 (en) 2015-02-20 2019-12-10 Rolls-Royce North American Technologies Inc. Wave rotor with piston assembly
US10393383B2 (en) 2015-03-13 2019-08-27 Rolls-Royce North American Technologies Inc. Variable port assemblies for wave rotors
US10641169B2 (en) 2017-06-09 2020-05-05 General Electric Company Hybrid combustor assembly and method of operation
US11674476B2 (en) 2017-06-09 2023-06-13 General Electric Company Multiple chamber rotating detonation combustor
US10969107B2 (en) 2017-09-15 2021-04-06 General Electric Company Turbine engine assembly including a rotating detonation combustor

Also Published As

Publication number Publication date
DE2254776B2 (de) 1977-03-10
DE2254776A1 (de) 1974-05-09
BE806396A (fr) 1974-02-15
JPS4995052A (US20020128544A1-20020912-P00008.png) 1974-09-10
IT998857B (it) 1976-02-20
NL169774B (nl) 1982-03-16
CA995638A (en) 1976-08-24
NL7314510A (US20020128544A1-20020912-P00008.png) 1974-04-29
DK141131C (US20020128544A1-20020912-P00008.png) 1980-06-30
JPS5520080B2 (US20020128544A1-20020912-P00008.png) 1980-05-30
FR2204756B1 (US20020128544A1-20020912-P00008.png) 1977-06-24
NL169774C (nl) 1982-08-16
AT324048B (de) 1975-08-11
DK141131B (da) 1980-01-21
GB1434253A (en) 1976-05-05
CH550937A (de) 1974-06-28
FR2204756A1 (US20020128544A1-20020912-P00008.png) 1974-05-24
SE407442B (sv) 1979-03-26

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