EP0157794A1 - Systeme generateur d'energie hydraulique a turbine a air sous pression dynamique - Google Patents

Systeme generateur d'energie hydraulique a turbine a air sous pression dynamique

Info

Publication number
EP0157794A1
EP0157794A1 EP84903328A EP84903328A EP0157794A1 EP 0157794 A1 EP0157794 A1 EP 0157794A1 EP 84903328 A EP84903328 A EP 84903328A EP 84903328 A EP84903328 A EP 84903328A EP 0157794 A1 EP0157794 A1 EP 0157794A1
Authority
EP
European Patent Office
Prior art keywords
pump
control
pressure
compensator
control piston
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.)
Withdrawn
Application number
EP84903328A
Other languages
German (de)
English (en)
Other versions
EP0157794A4 (fr
Inventor
Albert L. Markunas
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.)
Sundstrand Corp
Original Assignee
Sundstrand Corp
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 Sundstrand Corp filed Critical Sundstrand Corp
Publication of EP0157794A1 publication Critical patent/EP0157794A1/fr
Publication of EP0157794A4 publication Critical patent/EP0157794A4/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B17/00—Pumps characterised by combination with, or adaptation to, specific driving engines or motors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B49/00—Control, e.g. of pump delivery, or pump pressure of, or safety measures for, machines, pumps, or pumping installations, not otherwise provided for, or of interest apart from, groups F04B1/00 - F04B47/00
    • F04B49/08—Regulating by delivery pressure

Definitions

  • This invention pertains to a ram air turbine driven hydraulic power system wherein a variable displacement pump is driven by a ram air turbine and a pressure compensator valve is used for controlling displacement of the pump and for reducing pump displacement to prevent stall of the turbine upon decrease in turbine speed.
  • a conventional ram air turbine for driving a pump to provide emergency hydraulic power for an aircraft is designed to provide a specified hydraulic power at some minimum specified airspeed.
  • the ram air turbine has a plurality of variable pitch blades mounted in a hub.
  • the governor for the ram air turbine controls the pitch of the turbine blades to control rotational speed of the turbine under normal conditions of varying hydraulic load demand by the system and airspeed. Because of size and weight considerations, there is very little adjustment of the blade pitch available beyond the design point to allow the governor to control rotational speed of the turbine under reduced airspeed conditions. Once the blade pitch limit is reached, the ram air turbine operates as a fixed pitch unit.
  • a conventional pressure compensated variable displacement hydraulic pump used in the hydraulic power system for an aircraft has a maximum power absorption characteristic which is essentially proportional to rotational speed. Operation of such a pump for airspeeds more than approximately 5% below the design air speed will stall the ram air turbine driving the pump rotational speed to zero. Unless the air speed is increased to the design point, any attempt to bring the ram air turbine back into operation will only result in another stall, with the resultant loss of hydraulic power. This problem has led aircraft manufacturers to overspecify the requirements for the ram air turbine driven hydraulic power system, resulting in a size and weight penalty.
  • a primary feature of the invention is to provide a ram air turbine driven hydraulic power system for an aircraft utilizing a variable displacement pump wherein the displacement of the pump is controlled to provide a maximum power absorption characteristic for the pump that is approximately linear with rotational speed of the pump above a design set point and follows a speed cubed relationship below the design point to provide a power absorption characteristic for the pump below the design point, that essentially follows the stall line of the ram air turbine as the airspeed decreases with a constant stall margin to result in a no-stall ram air turbine hydraulic power system.
  • Another feature of the invention is to provide, in combination, a variable displacement pump and a ram air turbine for driving the pump with means for controlling the displacement of the pump to prevent stall of the ram air turbine including a pilot valve having a valve member for hydraulically controlling the displacement of the pump and being positionable by a compensator spring acting on the valve member in opposition to pump discharge pressure, and means responsive to the speed of the pump for varying the effective force of the compensator spring.
  • An additional feature of the invention is to provide a pressure compensator valve for a pump, said valve comprising a pilot valve with a movable valve member having a pilot responsive to discharge pressure of the pump and a compensator spring acting on the valve member in opposition to the pump discharge pressure and the improvement in the pressure compensator valve comprising a movable control piston engaging the compensator spring, a pair of control springs acting in opposition on said control piston, and means for applying a control pressure proportional to the square of pump speed to said control piston to control the position thereof and establish a force which results in a pressure set point for the pump which is a function of the compensator valve geometry and spring rates and increases linearly with the control pressure.
  • Still another feature of the invention is to provide a pressure compensator valve for controlling the displacement of a variable displacement pump driven by a ram air turbine to have the pump operate below a design point at progressively decreasing power absorption levels which stay within the progressively decreasing power generating levels of the ram air turbine
  • a displacement actuator for the pump a pilot valve member positionable for controlling the displacement, actuator, a compensator spring urging the pilot valve member in a first direction and the pilot valve member subject to pump discharge pressure acting in opposition to the compensator spring, and means for varying the set point at which the pressure compensator valve will operate to destroke the pump comprising, a control piston having a range of movement between two limit positions and movably supporting an end of the compensator spring, a pair of control springs acting in opposition on the control piston, and means for applying a control pressure proportional to the square of the pump speed to the control piston which acts to set the position of the control piston and control the force of the compensator spring.
  • Fig. 1 is a schematic view of the ram air turbine hydraulic power system
  • Fig. 2 is a central sectional view of the pressure compensator valve
  • Fig. 3 is a graph plotting ram air turbine power against ram air turbine speed and showing stall characteristics of the ram air turbine and power absorption characteristics of the variable displacement pump at various flight speeds.
  • the ram air turbine hydraulic power system is shown generally in Fig. 1 wherein a ram air turbine, indicated generally at 10, drives a variable displacement pump 12 through suitable drive connections including a drive shaft 14.
  • a ram air turbine drives a variable displacement pump 12 through suitable drive connections including a drive shaft 14.
  • the variable displacement pump 12 may be of the type having a series of pistons whose stroke is controlled by a hanger with a face cam.
  • a displacement control for the hanger includes a cylinder 20 having an actuator piston 22 connected to the hanger for setting the position thereof.
  • a pressure compensator valve is connected by a line 26 to the pump discharge line 18 to sense pump discharge pressure and controls the communication of the actuator piston 22 with either pump discharge through a line 28 or case drain, indicated at 30.
  • the pressure compensated valve 24 also receives a control pressure through a line 32 which connects to a unit 34 which senses the speed of the shaft 14 and, therefore, the speed of the pump 12 and provides an output control pressure which is proportional to the square of pump speed.
  • the pressure compensator valve is shown particularly in Fig. 2 and has a body 40 having a pilot valve with a pilot valve member 42 having a central land 44 which controls communication of the actuator piston 22 through line 28 with either pump discharge existing at the upper end of the pressure compensator valve body or to case drain 30.
  • the pilot valve member 42 is at a pressure set point wherein the land 44 is positioned to block communication of the actuator piston line 28 with both pump discharge and case drain whereby the actuator piston is neither stroked nor destroked.
  • the pilot valve member 42 has a land 46 at the upper end thereof providing a pilot section responsive to pump discharge pressure.
  • the pump discharge pressure urges the pilot, valve member in a direction to connect pump discharge with the actuator piston 22.
  • This force is opposed by a compensator spring 50 which, at one end, engages an end 52 of the pilot valve member.
  • the structure of the pressure compensator valve, as so far described, is conventional.
  • the pressure compensator valve embodying the invention has a control piston 54 mounted within a chamber 56 of the valve body 40 for movement between a pair of stops defined by end walls 58 and 60 of the chamber 56, and which provide limit positions for movement of the control piston 54 from the position shown in Fig. 2.
  • the control piston 54 movably supports the compensator spring 50 by a transverse wall 62 of the control piston engaging an end of the compensator spring 50.
  • a pair of control springs 70 and 72 are positioned within the body chamber 56 and act in opposition on the control piston, with the control spring 70 positioned between the end wall 58 of the body chamber and the transverse wall 62 of the control piston.
  • the control spring 72 is positioned between the transverse wall 62 of the control piston and the end wall 60.
  • the control pressure which is responsive to the speed of the pump and, more particularly, which is proportional to the square of pump speed, enters the body chamber 56 from the control pressure line 32 and acts on the annular end of the control piston wall 76 and the transverse wall 62 of the control piston.
  • the pressure compensator valve provides a pump maximum power absorption characteristic that is approximately linear with rotational speed above the design point and follows a speed cubed relationship below the design point.
  • Fig. 3 the relationship between ram air turbine power and ram air turbine speed at various flight speeds of the aircraft is shown by the curves 80, 82, 84, 86 and 88 representing increasing flight speeds, and with the curve 86 illustrating the relation at the approximate normal cruise speed of the aircraft.
  • the stall line for the ram air turbine is shown at 90 which indicates the speed at which the ram air turbine will stall at a particular power requirement on the ram air turbine. As the ram air turbine speed decreases, the available power without stall decreases.
  • the power absorption curve for the pump 12 is illustrated by a straight line 92 above a design point 94 for the operation of the pump and by a curve 96 below the design point showing a power absorption characteristic below the design point that is a cubic function of the pump speed.
  • the pilot valve 24 controls the flow of oil to and from the actuator piston 22 to either destroke or stroke the pump 12 which results in less or more pump delivery to either lower or raise the pump discharge pressure.
  • the control is achieved by a force balance and the pump discharge pressure which will neither stroke nor destroke the actuator piston 22 is the pressure set point and is determined by the diameter of the land 46 providing the pilot section and by the force of the compensator spring 50.
  • a primary feature is the control of the compensator spring force which is determined by the position of the control piston 54 relative to the pilot valve member 42. The position of the control piston 54 is dependent on the forces in the control springs 70 and 72, the force in the compensator spring 50, and the. value of the control pressure representing pump speed. Therefore, the pressure set point is a function of the compensator valve geometry and the spring rates and increases linearly with the control pressure representative of pump speed.
  • the control piston For low values of the control pressure, the control piston is on the stop defined by end wall 60 at one limit position and the pressure set point is constant at some low value.
  • the control piston 54 is on the stop defined by end wall 58 at the other limit position and the pressure set point is constant at the nominal design pressure of the pump.
  • the pressure compensator valve 24 acts like a conventional compensator valve.
  • the pressure compensator valve is a variable pressure set point valve, with the pressure set point being linearly dependent on the control pressure. During operation as the flight speed drops below the design point, the speed of the ram air turbine would begin to drop causing the control pressure delivered to the pressure compensator valve to drop.
  • the pump discharge pressure required to overcome the compensator spring 50 drops, thus allowing oil to flow to the actuator piston 22.
  • This destrokes the pump resulting in a lower system pressure corresponding to the lower airspeed and reducing the pump horsepower demand to match the horsepower available from the ram air turbine.
  • the curve 96 representing the power absorption of the pump 12 below the design point is offset from the stall line 90 for the ram air turbine, to provide a constant margin to assure that the ram air turbine will not stall as flight speed reduces.
  • the control pressure applied to the pressure compensator valve must be made proportional to the square of pump speed. This is shown in Fig.
  • the unit 34 can be a commercially available unit which would electronically sense the speed of the pump and control an electro-hydraulic servo valve to set the control pressure.
  • the unit 34 There are a number of alternatives to the unit 34. These alternatives include the use of a small fixed displacement gear pump driven by the ram air turbine 10 with the discharge from this pump passing through an orifice provided in the transverse wall 62 of the control piston 54.
  • a second alternative would be adding a small centrifugal stage pump driven by the ram air turbine 10 with its outlet applied against the control piston.
  • a third alternative would be the use of a small weight arranged to generate a force varying with the square of pump speed to be used in a pressure servo to generate the control pressure.
  • the ram air turbine hydraulic power system provides for reduced power demand by a variable displacement pump as the air speed causing operation of the ram air turbine reduces thus avoiding the sudden loss of hydraulic power during some unforeseen flight condition of the aircraft.
  • valve land 44 of the pressure compensator valve is positioned as shown in
  • valve land 44 will move to the position to block communication with line 28. Subsequent increase in aircraft speed back to the design point will increase the control pressure acting on the control piston 54 to raise the valve land above the position shown in Fig. 2 whereby oil can flow from the actuator piston 22 to the case drain 30 and when a force balanced condition is achieved, the land 44 has returned to the position of Fig. 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Positive-Displacement Pumps (AREA)

Abstract

Système générateur d'énergie hydraulique à turbine à air sous pression dynamique et soupape de compensation de pression (24) servant à réguler le déplacement d'une pompe à déplacement variable (12) entraînée par une turbine à air sous pression dynamique (10). La soupape de compensation de pression possède un organe de soupape (42) pourvu d'un pilote réagissant à la pression de décharge de la pompe et un ressort compensateur (50) agissant sur l'organe de soupape en opposition à la pression de décharge, un piston de commande mobile (54) en prise avec le ressort compensateur, une paire de ressorts de commande (70, 72) en prise avec le piston de commande et agissant l'un contre l'autre. Une pression de commande proportionnelle au carré de la vitesse de la pompe est appliquée sur le piston de commande, faisant varier la force du ressort compensateur en fonction de la position du piston de commande.
EP19840903328 1983-09-16 1984-08-27 Systeme generateur d'energie hydraulique a turbine a air sous pression dynamique. Withdrawn EP0157794A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US53283983A 1983-09-16 1983-09-16
US532839 1983-09-16

Publications (2)

Publication Number Publication Date
EP0157794A1 true EP0157794A1 (fr) 1985-10-16
EP0157794A4 EP0157794A4 (fr) 1986-02-10

Family

ID=24123389

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19840903328 Withdrawn EP0157794A4 (fr) 1983-09-16 1984-08-27 Systeme generateur d'energie hydraulique a turbine a air sous pression dynamique.

Country Status (5)

Country Link
EP (1) EP0157794A4 (fr)
JP (1) JPS60502221A (fr)
DE (1) DE3490419T1 (fr)
GB (1) GB2157461B (fr)
WO (1) WO1985001326A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0367476A1 (fr) * 1988-11-02 1990-05-09 Vickers Systems Limited Pompes à déplacement variable
JP2578371B2 (ja) * 1989-09-22 1997-02-05 株式会社小松製作所 可変容量ポンプの容量制御装置
GB9119448D0 (en) * 1991-09-12 1991-10-23 Vickers Systems Ltd System controls
WO2000059780A2 (fr) * 1999-04-01 2000-10-12 Hamilton Sundstrand Corporation Unite generatrice de pics de puissance a volant cinetique pour le systeme hydraulique d'un avion
CA2762184A1 (fr) 2009-05-12 2010-11-18 Icr Turbine Engine Corporation Systeme de stockage et de conversion d'energie de turbine a gaz
US8866334B2 (en) 2010-03-02 2014-10-21 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
US8984895B2 (en) 2010-07-09 2015-03-24 Icr Turbine Engine Corporation Metallic ceramic spool for a gas turbine engine
EP2612009B1 (fr) 2010-09-03 2020-04-22 ICR Turbine Engine Corporatin Moteur à turbine à gaz
US9045983B2 (en) 2010-10-19 2015-06-02 Hamilton Sundstrand Corporation Turbine yokeplate flyweights to improve RAT startup
US9188105B2 (en) 2011-04-19 2015-11-17 Hamilton Sundstrand Corporation Strut driveshaft for ram air turbine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1528550A1 (de) * 1964-09-22 1969-09-25 Sperry Rand Corp Hydraulisches Zufuehrungs- und Steuersystem
DE3220782A1 (de) * 1982-06-02 1983-12-08 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Einrichtung zum optimieren des energiehaushaltes von flugzeugbetaetigungssystemen

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3543508A (en) * 1968-10-16 1970-12-01 Hyster Co Hydrostatic transmission with pressure control
US3637327A (en) * 1969-11-24 1972-01-25 Borg Warner Pump
US3907221A (en) * 1970-09-28 1975-09-23 Garrett Corp Ram fluid turbine
US3784328A (en) * 1972-06-13 1974-01-08 Sperry Rand Corp Power transmission
US3946689A (en) * 1974-07-26 1976-03-30 Robbins Albert H Air dynamo pressure regulation and modulation device for surface effect ships and air cushion vehicles
US4103489A (en) * 1977-04-15 1978-08-01 Deere & Company Total power fluid system
US4274257A (en) * 1979-01-08 1981-06-23 Eaton Corporation Anti-stall controller
US4355509A (en) * 1979-12-31 1982-10-26 Sundstrand Corporation Split torque transmission control
US4355510A (en) * 1980-09-12 1982-10-26 Caterpillar Tractor Co. Unloading means for flow-pressure compensated valve

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1528550A1 (de) * 1964-09-22 1969-09-25 Sperry Rand Corp Hydraulisches Zufuehrungs- und Steuersystem
DE3220782A1 (de) * 1982-06-02 1983-12-08 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Einrichtung zum optimieren des energiehaushaltes von flugzeugbetaetigungssystemen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO8501326A1 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine

Also Published As

Publication number Publication date
EP0157794A4 (fr) 1986-02-10
DE3490419T1 (de) 1985-09-19
GB8512204D0 (en) 1985-06-19
GB2157461B (en) 1987-04-15
WO1985001326A1 (fr) 1985-03-28
GB2157461A (en) 1985-10-23
JPS60502221A (ja) 1985-12-19

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Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19850521

AK Designated contracting states

Designated state(s): FR

A4 Supplementary search report drawn up and despatched

Effective date: 19860210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Withdrawal date: 19870218

RIN1 Information on inventor provided before grant (corrected)

Inventor name: MARKUNAS, ALBERT, L.