US20130039781A1 - Anticipation logic for a surge control valve utilized with load compressor - Google Patents

Anticipation logic for a surge control valve utilized with load compressor Download PDF

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Publication number
US20130039781A1
US20130039781A1 US13/204,916 US201113204916A US2013039781A1 US 20130039781 A1 US20130039781 A1 US 20130039781A1 US 201113204916 A US201113204916 A US 201113204916A US 2013039781 A1 US2013039781 A1 US 2013039781A1
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United States
Prior art keywords
surge control
compressor
control
surge
set forth
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.)
Abandoned
Application number
US13/204,916
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English (en)
Inventor
Victor Pascu
Nipulkumar G. Shah
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Hamilton Sundstrand Corp
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Hamilton 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 Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Priority to US13/204,916 priority Critical patent/US20130039781A1/en
Assigned to HAMILTON SUNDSTRAND CORPORATION reassignment HAMILTON SUNDSTRAND CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PASCU, VICTOR, SHAH, NIPULKUMAR G.
Priority to FR1257661A priority patent/FR2978994B1/fr
Publication of US20130039781A1 publication Critical patent/US20130039781A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0223—Control schemes therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • 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
    • F05D2270/00—Control
    • F05D2270/40—Type of control system
    • F05D2270/44—Type of control system active, predictive, or anticipative

Definitions

  • This application relates generally to a method to optimize the operation of a compressor which delivers pneumatic power in order to maximize performance and maintaining proper stability margin for both steady state and transient operation.
  • An APU is a small gas turbine engine that provides a number of functions associated with an aircraft other than propulsion, particularly before the main aircraft engines are started.
  • Some APU configurations include a shaft-mounted load compressor which delivers pneumatic power to aircraft accessories.
  • Load compressor bleed air is delivered to aircraft systems through a bleed control valve. Some of the air may be utilized as cabin air before the main gas turbine engines are started, and the load compressor may also supply air to the main gas turbine engines at start-up.
  • the APU-supplied accessories have a wide range of compressed air requirements, which the APU bleed control valve has to accommodate. If the air demand drops below certain limits an unstable operation on the compressor, called “surge” may occur.
  • an anti-surge valve To maintain the compressor flow above its surge level an anti-surge valve is used.
  • the engine is programmed with anti-surge logic to modulate the anti-surge valve to divert a portion of the compressor flow to the atmosphere and therefore to maintain the compressed air flow above minimum limits to avoid surge.
  • the compressor minimum air flow limits are set taking into account numerous parameters including operating conditions, compressor inlet guided vanes position, bleed demands, etc. Another important aspect which is considered is the operation during transient maneuvers. During a fast reduction of the air flow requirement, the compressor minimum air flow could drop momentarily below the minimum limit and cause surge.
  • the minimum bleed flow limit has to be raised.
  • a higher minimum bleed flow limit reduces in certain operating conditions the APU performance, increasing the engine temperature and fuel consumption and, in the same time, reducing the bleed air quality, lower bleed pressure and flow.
  • a load compressor includes an air inlet and an outlet, a bleed valve and an anti-surge valve positioned on the outlet.
  • the bleed valve serves to selectively pass air to a downstream use while the anti-surge valve dumps it to atmosphere.
  • a control for the compressor and the surge control valve is also included.
  • the control is provided with a variable indicative of the operation of the load compressor, the variable being indicative of movement to transient operation of the compressor.
  • the control is provided with a low surge control limit for steady state operation, and a higher surge control limit The low and higher surge control limits are utilized to control the opening of the surge control valve.
  • An aircraft air supply system and a method are also disclosed.
  • FIG. 1A schematically shows a load compressor for an aircraft.
  • FIG. 1B shows another embodiment.
  • FIG. 2 shows operating conditions
  • FIG. 3 is a flowchart of an inventive logic.
  • FIG. 1A schematically shows a load compressor 24 , APU 22 , and aircraft use 32 as a combined system 20 .
  • APU 22 typically includes a small gas turbine engine that provides electricity, but also drives load compressor 24 .
  • the load compressor 24 has an air inlet 26 , and delivers the air through an outlet 21 , and through a combined surge control and bleed valve 28 to a downstream use 32 .
  • the downstream use is typically associated with an aircraft, and may include the aircraft passenger cabin, as well as the main gas turbine engines on the aircraft.
  • a controller 29 controls compressor 24 and the valve 28 .
  • the surge control valve When the surge control valve is open, it directs a portion of the compressed air to a dump 30 where the compressed air is returned to atmosphere. Other air is directed into line 34 and to use 32 . So-called “fast-acting” valves may be utilized for surge control valve 28 .
  • the valve 28 is a valve which can divert a portion of the flow to the dump line 30 , and another portion to line 34 .
  • the control 29 controls the valve 28 to divert at least a portion of the air to the dump line 30 .
  • FIG. 1B shows an embodiment 120 which is somewhat similar to the FIG. 1A embodiment.
  • Each of the elements which are identical to the FIG. 1A embodiment are included with 100 added to the reference number.
  • the control 129 works in combination with the load compressor 124 .
  • the load compressor 124 receives air from inlet 126 , and delivers it through outlet 121 to a downstream use 132 .
  • the APU 122 drives the load compressor 124 .
  • the use 132 receives air from a line 134 .
  • What is different in the FIG. 1B embodiment is the single valve has been replaced with a bleed valve 131 , and an anti-surge valve 128 . The two valves were combined in the valve 28 of FIG. 1A .
  • the anti-surge valve 128 is controlled to open and dump air to atmosphere 130 should the surge limits be exceeded, as will be explained below. When closed, the anti-surge valve 128 allows air to be passed from the outlet of load compressor 124 to downstream use 132 as further limited by bleed valve 131 .
  • the prior art control of a phenomenon known as surge margin can be described by the operating conditions shown in FIG. 2 .
  • the line X shows operational points for a typical load compressor.
  • a first higher surge control limit is shown at Y.
  • a second lower surge control limit is shown at Z.
  • T 1 for example
  • LDC DPP load compressor dynamic head measurement
  • T 2 existing pressure sensors located in a load compressor diffuser and another in the load compressor exit may be used. The difference between the two pressures would be indicative of the LDC DPP. Of course, other ways of sensing the pressure may be used.
  • the LDC DPP is generally inversely proportional to the discharge pressure from the compressor.
  • T 2 is generally shown at the upper surge control limit Y.
  • Another point, T 3 is also illustrated.
  • this limit may not be acceptable for fast transient operations, such as startup of a main gas turbine engine on an aircraft receiving APU 22 / 122 .
  • the present invention provides a control logic which anticipates a movement to transient operation, and a need for the higher limit.
  • variable LDC DPP is proportional to flow (and inversely proportional to pressure)
  • a drop in the LDC DPP, or a negative derivative or slope would be indicative of the movement towards surge.
  • a control logic which may be included in control 29 , 129 , looks for change in the variable. If the change exceeds a limit, then the higher surge control limit is utilized. On the other hand, if the change does not exceed the limit, then the lower surge control limit is utilized.
  • a threshold for the change in LDC DPP may be if the rate of change is below ⁇ 2% per second, for example.
  • the threshold limit may be function of engine speed, inlet guide vane position or other operating condition.
  • the logic may require that there be consecutive readings below this threshold. For example, readings could be taken every 20 millisecond, and only when a particular number of consecutive readings, three for example, are below this threshold would trigger the surge control limit be changed from the steady state low value to the high transient value.
  • the numeric values are purely examples. Any other rate of change, timing between readings, or number of consecutive readings can be utilized.
  • the system will return to the lower steady state limit once the amount of change is reduced such that a new steady state condition appears to have been reached.
  • the anti-surge control logic may overcome the time lag of anti-surge valve control and operation by commencing the valve opening before the steady state limit is reached.
  • the anti-surge control logic will detect a high delta between the compressor operating point and the transient limit (limit Y).
  • the control can generate a higher opening command to accelerate the valve opening.
  • the signal to the valve may be increased proportionally based upon the magnitude of the error.
  • APU performance may be improved and fuel consumption reduced. While a load compressor operating with an APU is disclosed, the features of the application may be beneficial in other types of compressors.
US13/204,916 2011-08-08 2011-08-08 Anticipation logic for a surge control valve utilized with load compressor Abandoned US20130039781A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US13/204,916 US20130039781A1 (en) 2011-08-08 2011-08-08 Anticipation logic for a surge control valve utilized with load compressor
FR1257661A FR2978994B1 (fr) 2011-08-08 2012-08-07 .

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/204,916 US20130039781A1 (en) 2011-08-08 2011-08-08 Anticipation logic for a surge control valve utilized with load compressor

Publications (1)

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US20130039781A1 true US20130039781A1 (en) 2013-02-14

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US (1) US20130039781A1 (fr)
FR (1) FR2978994B1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140130510A1 (en) * 2012-11-09 2014-05-15 Honeywell International Inc. Systems and methods for directing cooling flow into the surge plenum of an exhaust eductor cooling system
WO2018060531A1 (fr) * 2016-09-29 2018-04-05 Airbus Operations, S.L. Alimentation auxiliaire en air pour un aéronef
CN112937885A (zh) * 2021-03-04 2021-06-11 中国商用飞机有限责任公司 一种利用辅助动力装置进行引气的引气系统以及引气控制方法
US11339721B2 (en) 2018-11-14 2022-05-24 Honeywell International Inc. System and method for supplying compressed air to a main engine starter motor

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4370560A (en) * 1979-10-15 1983-01-25 Sundstrand Corporation Compressor load control for an auxiliary power unit
US4594050A (en) * 1984-05-14 1986-06-10 Dresser Industries, Inc. Apparatus and method for detecting surge in a turbo compressor
US4834622A (en) * 1983-06-15 1989-05-30 Sundstrand Corporation Gas turbine engine/load compressor power plants
US4944652A (en) * 1988-02-18 1990-07-31 Man Gutehoffnungshutte Gmbh Process and device for the control of turbo compressors
US5240380A (en) * 1991-05-21 1993-08-31 Sundstrand Corporation Variable speed control for centrifugal pumps
US5265408A (en) * 1992-02-13 1993-11-30 Allied-Signal Inc. Exhaust eductor cooling system
US5306116A (en) * 1992-04-10 1994-04-26 Ingersoll-Rand Company Surge control and recovery for a centrifugal compressor
US5309708A (en) * 1988-06-03 1994-05-10 Alliedsignal Inc. Multifunction integrated power unit
US5508943A (en) * 1994-04-07 1996-04-16 Compressor Controls Corporation Method and apparatus for measuring the distance of a turbocompressor's operating point to the surge limit interface
US20080019842A1 (en) * 2006-07-21 2008-01-24 Hamilton Sundstrand Corporation System and method for controlling compressor flow
US7513119B2 (en) * 2005-02-03 2009-04-07 The Boeing Company Systems and methods for starting aircraft engines

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4900232A (en) * 1983-10-07 1990-02-13 The Babcock & Wilcox Company Compressor surge control method
US4697980A (en) * 1984-08-20 1987-10-06 The Babcock & Wilcox Company Adaptive gain compressor surge control system
DE102004035575A1 (de) * 2004-07-22 2006-02-16 Daimlerchrysler Ag Verfahren und Vorrichtung zur Steuerung einer Brennkraftmaschine mit einem Verdichter, insbesondere eines Abgasturboladers

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4370560A (en) * 1979-10-15 1983-01-25 Sundstrand Corporation Compressor load control for an auxiliary power unit
US4834622A (en) * 1983-06-15 1989-05-30 Sundstrand Corporation Gas turbine engine/load compressor power plants
US4594050A (en) * 1984-05-14 1986-06-10 Dresser Industries, Inc. Apparatus and method for detecting surge in a turbo compressor
US4944652A (en) * 1988-02-18 1990-07-31 Man Gutehoffnungshutte Gmbh Process and device for the control of turbo compressors
US5309708A (en) * 1988-06-03 1994-05-10 Alliedsignal Inc. Multifunction integrated power unit
US5240380A (en) * 1991-05-21 1993-08-31 Sundstrand Corporation Variable speed control for centrifugal pumps
US5265408A (en) * 1992-02-13 1993-11-30 Allied-Signal Inc. Exhaust eductor cooling system
US5306116A (en) * 1992-04-10 1994-04-26 Ingersoll-Rand Company Surge control and recovery for a centrifugal compressor
US5508943A (en) * 1994-04-07 1996-04-16 Compressor Controls Corporation Method and apparatus for measuring the distance of a turbocompressor's operating point to the surge limit interface
US7513119B2 (en) * 2005-02-03 2009-04-07 The Boeing Company Systems and methods for starting aircraft engines
US20080019842A1 (en) * 2006-07-21 2008-01-24 Hamilton Sundstrand Corporation System and method for controlling compressor flow

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Boyce, Meherwan P., William R. Bohannan, Royce N. Brown, John R. Gaston, Cyrus Meher-Homji, Robert H. Meier, and Norbert E. Pobanz. "TUTTORIAL SESSION ON PRACTICAL APPROACH TO SURGE AND SURGE CONTROL." TWELFTH TURBO MACHINERY SYMPOSIUM. TEXAS A&M UNIVERSITY. N.p.: n.p., 1983. 147-73. Print. Conference Proceedings *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140130510A1 (en) * 2012-11-09 2014-05-15 Honeywell International Inc. Systems and methods for directing cooling flow into the surge plenum of an exhaust eductor cooling system
WO2018060531A1 (fr) * 2016-09-29 2018-04-05 Airbus Operations, S.L. Alimentation auxiliaire en air pour un aéronef
US11091271B2 (en) 2016-09-29 2021-08-17 Airbus Operations S.L. Auxiliary air supply for an aircraft
US11339721B2 (en) 2018-11-14 2022-05-24 Honeywell International Inc. System and method for supplying compressed air to a main engine starter motor
CN112937885A (zh) * 2021-03-04 2021-06-11 中国商用飞机有限责任公司 一种利用辅助动力装置进行引气的引气系统以及引气控制方法

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Publication number Publication date
FR2978994B1 (fr) 2014-10-10
FR2978994A1 (fr) 2013-02-15

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Date Code Title Description
AS Assignment

Owner name: HAMILTON SUNDSTRAND CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:PASCU, VICTOR;SHAH, NIPULKUMAR G.;REEL/FRAME:026714/0186

Effective date: 20110808

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION