GB201403954D0 - Multi-engine performance margin synchronization adaptive control system and method - Google Patents

Multi-engine performance margin synchronization adaptive control system and method

Info

Publication number
GB201403954D0
GB201403954D0 GB201403954A GB201403954A GB201403954D0 GB 201403954 D0 GB201403954 D0 GB 201403954D0 GB 201403954 A GB201403954 A GB 201403954A GB 201403954 A GB201403954 A GB 201403954A GB 201403954 D0 GB201403954 D0 GB 201403954D0
Authority
GB
United Kingdom
Prior art keywords
control system
adaptive control
engine performance
performance margin
synchronization adaptive
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.)
Granted
Application number
GB201403954A
Other versions
GB2515141B (en
GB2515141A (en
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.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
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
Priority claimed from US13/870,302 external-priority patent/US9458771B2/en
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Publication of GB201403954D0 publication Critical patent/GB201403954D0/en
Publication of GB2515141A publication Critical patent/GB2515141A/en
Application granted granted Critical
Publication of GB2515141B publication Critical patent/GB2515141B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F02C6/02—Plural gas-turbine plants having a common power output
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/42—Control of fuel supply specially adapted for the control of two or more plants simultaneously
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • 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
    • F05D2270/01—Purpose of the control system
    • F05D2270/13—Purpose of the control system to control two or more engines simultaneously
GB1403954.9A 2013-03-25 2014-03-06 Multi-engine performance margin synchronization adaptive control system and method Expired - Fee Related GB2515141B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361804836P 2013-03-25 2013-03-25
US13/870,302 US9458771B2 (en) 2013-03-25 2013-04-25 Multi-engine performance margin synchronization adaptive control system and method

Publications (3)

Publication Number Publication Date
GB201403954D0 true GB201403954D0 (en) 2014-04-23
GB2515141A GB2515141A (en) 2014-12-17
GB2515141B GB2515141B (en) 2015-10-21

Family

ID=50554609

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1403954.9A Expired - Fee Related GB2515141B (en) 2013-03-25 2014-03-06 Multi-engine performance margin synchronization adaptive control system and method

Country Status (1)

Country Link
GB (1) GB2515141B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110621858A (en) * 2017-04-03 2019-12-27 赛峰直升机发动机公司 Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3037923B1 (en) 2015-06-23 2018-05-04 Airbus Helicopters METHOD FOR CONTROLLING A TRIMOTIVE MOTOR INSTALLATION FOR A ROTARY WING AIRCRAFT
US20170159574A1 (en) * 2015-12-04 2017-06-08 General Electric Company Adaptive Engine Model Torque Splitting Optimization

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4644744A (en) * 1985-04-19 1987-02-24 Allied Corporation Control device for controlling an engine of a turbine power system having more than one engine
FR2902408B1 (en) * 2006-06-19 2008-08-08 Eurocopter France POWER BALANCING OF TWO TURBOMOTORS OF AN AIRCRAFT

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110621858A (en) * 2017-04-03 2019-12-27 赛峰直升机发动机公司 Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

Also Published As

Publication number Publication date
GB2515141B (en) 2015-10-21
GB2515141A (en) 2014-12-17

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20200306