Inventor · disambiguated record
Rodolphe Dudebout
Also filed as: DUDEBOUT RODOLPHE
31 granted patents·11 pending applications·410 citations·filing 2001–2023
97Inventor score
Top patents by PatentIndex Score
42 records- 0195US12092032B1Gas turbine engine hydrogen supply system and methodHONEYWELL INT INC·Filed 2023·Granted Sep 17, 2024·3 cites·7 claims
- 0294US7185497B2Rich quick mix combustion systemHONEYWELL INT INC·Filed 2004·Granted Mar 6, 2007·111 cites·15 claims
- 0393US7506512B2Advanced effusion cooling schemes for combustor domesHONEYWELL INT INC·Filed 2005·Granted Mar 24, 2009·36 cites·33 claims
- 0491US11519604B2Plug resistant effusion holes for gas turbine engineHONEYWELL INT INC·Filed 2021·Granted Dec 6, 2022·2 cites·20 claims
- 0591US11085641B2Plug resistant effusion holes for gas turbine engineHONEYWELL INT INC·Filed 2018·Granted Aug 10, 2021·6 cites·13 claims
- 0690US9410702B2Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniquesHONEYWELL INT INC·Filed 2014·Granted Aug 9, 2016·15 cites·13 claims
- 0789US10895157B2Gas turbine engine components with air-cooling features, and related methods of manufacturing the sameHONEYWELL INT INC·Filed 2017·Granted Jan 19, 2021·5 cites·20 claims
- 0887US11959401B1Deswirl system for gas turbine engineHONEYWELL INT INC·Filed 2023·Granted Apr 16, 2024·2 cites·19 claims
- 0987US7665306B2Heat shields for use in combustorsHONEYWELL INT INC·Filed 2007·Granted Feb 23, 2010·26 cites·16 claims
- 1087US7546737B2Segmented effusion cooled gas turbine engine combustorHONEYWELL INT INC·Filed 2006·Granted Jun 16, 2009·27 cites·20 claims
- 1186US7500364B2System for coupling flow from a centrifugal compressor to an axial combustor for gas turbinesHONEYWELL INT INC·Filed 2005·Granted Mar 10, 2009·23 cites·10 claims
- 1284US9080770B2Reverse-flow annular combustor for reduced emissionsDUDEBOUT RODOLPHE·Filed 2011·Granted Jul 14, 2015·16 cites·19 claims
- 1383US6554562B2Combustor hot streak alignment for gas turbine engineHONEYWELL INT INC·Filed 2001·Granted Apr 29, 2003·47 cites·30 claims
- 1481US10166524B2Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2017·Granted Jan 1, 2019·1 cites·14 claims
- 1581US9400110B2Reverse-flow annular combustor for reduced emissionsHONEYWELL INT INC·Filed 2012·Granted Jul 26, 2016·9 cites·20 claims
- 1680US7926284B2Quench jet arrangement for annular rich-quench-lean gas turbine combustorsHONEYWELL INT INC·Filed 2006·Granted Apr 19, 2011·11 cites·18 claims
- 1777US7905094B2Combustor systems with liners having improved cooling hole patternsHONEYWELL INT INC·Filed 2007·Granted Mar 15, 2011·15 cites·18 claims
- 1875US7812282B2Methods of forming fan-shaped effusion holes in combustorsHONEYWELL INT INC·Filed 2007·Granted Oct 12, 2010·18 cites·19 claims
- 1973US9656229B2Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Granted May 23, 2017·1 cites·4 claims
- 2071US10775044B2Gas turbine engine dual-wall hot section structureHONEYWELL INT INC·Filed 2018·Granted Sep 15, 2020·2 cites·20 claims
- 2170US11306659B2Plug resistant effusion holes for gas turbine engineHONEYWELL INT INC·Filed 2019·Granted Apr 19, 2022·1 cites·20 claims
- 2270US10101030B2Gas turbine engines with plug resistant effusion cooling holesHONEYWELL INT INC·Filed 2014·Granted Oct 16, 2018·3 cites·18 claims
- 2369US10816211B2Axially staged rich quench lean combustion systemHONEYWELL INT INC·Filed 2017·Granted Oct 27, 2020·1 cites·20 claims
- 2461US11287133B2Axially staged rich quench lean combustion systemHONEYWELL INT INC·Filed 2020·Granted Mar 29, 2022·0 cites·20 claims
- 2559US7036321B2Auxiliary power unit having a rotary fuel slingerHONEYWELL INT INC·Filed 2004·Granted May 2, 2006·24 cites·19 claims
- 2657US2014058173A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 2757US2017015606A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2016·Application pending·0 cites
- 2855US8127554B2Quench jet arrangement for annular rich-quench-lean gas turbine combustorsZUPANC FRANK J·Filed 2007·Granted Mar 6, 2012·5 cites·16 claims
- 2950US11674686B2Coating occlusion resistant effusion cooling holes for gas turbine engineHONEYWELL INT INC·Filed 2021·Granted Jun 13, 2023·0 cites·18 claims
- 3049US12372239B2Gaseous fuel nozzle for use in gas turbine enginesHONEYWELL INT INC·Filed 2022·Granted Jul 29, 2025·0 cites·6 claims
- 3146US2014058174A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 3246US2014056771A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 3346US2014058172A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 3446US2014058176A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 3546US2014058169A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 3645US2014058178A1Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2013·Application pending·0 cites
- 3744US10029957B2Methane conversion apparatus and process using a supersonic flow reactorUOP LLC·Filed 2017·Granted Jul 24, 2018·0 cites·15 claims
- 3840US11988386B2Gas turbine engine injector module with thermally coupled fuel lines having respective outletsHONEYWELL INT INC·Filed 2021·Granted May 21, 2024·0 cites·16 claims
- 3940US11549437B2Combustor for gas turbine engine and method of manufactureHONEYWELL INT INC·Filed 2021·Granted Jan 10, 2023·0 cites·20 claims
- 4039US2007245710A1Optimized configuration of a reverse flow combustion system for a gas turbine engineHONEYWELL INT INC·Filed 2006·Application pending·0 cites
- 4134US2006037323A1Film effectiveness enhancement using tangential effusionHONEYWELL INT INC·Filed 2004·Application pending·0 cites
- 4232US2013219911A1Combustion system for a gas turbine engine and method for directing fuel flow within the sameDUDEBOUT RODOLPHE·Filed 2012·Application pending·0 cites
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Identity basis: PatentsView inventor disambiguation (2025Q4-odp release). How scoring works →