-
公开(公告)号：US20220268213A1
公开(公告)日：2022-08-25
申请号：US17179829
申请日：2021-02-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO , Sandeep Singh DHALLA
Abstract: A fuel supply system for a gas turbine engine comprises a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler has an upstream end and downstream end relative to a fuel flow direction along a fuel nozzle longitudinal axis. The fuel swirler has a first axial fuel passage along the longitudinal axis in fluid communication with a first fuel supply and terminating at a first fuel outlet at the downstream end, a second axial fuel passage along the longitudinal axis in fluid communication with a second fuel supply and terminating at a second fuel outlet at the downstream end, and a plurality of compressed air outlets at the downstream end. The first fuel outlet is positioned on an outermost surface of the fuel swirler and leads directly to a mixing site downstream of the fuel swirler.
-
公开(公告)号：US20140318145A1
公开(公告)日：2014-10-30
申请号：US14169618
申请日：2014-01-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Bhawan B. PATEL , Oleg MORENKO
IPC: F02C7/22
Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.
Abstract translation: 提供了一种用于提高对飞行器供电的燃气涡轮发动机的燃烧器的燃烧效率的方法。 该方法包括选择性地使用两种不同的燃料喷射单元或其组合来在燃气涡轮发动机的燃烧器的燃烧室中喷射燃料。 针对高功率需求选择和优化了两种不同的燃料喷射单元中的第一种，而针对低功率水平要求选择并优化了两种不同燃料喷射单元中的第二种。 在操作中，两个不同喷射单元之间的燃料流量比被控制为功率水平要求的函数。
-
公开(公告)号：US20230358145A1
公开(公告)日：2023-11-09
申请号：US17662143
申请日：2022-05-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Hervé TURCOTTE , Kenneth PARKMAN , Oleg MORENKO , Nicholas GUGLIELMIN , Gavin KISUN , Ryan MISKIE
CPC classification number: F01D9/065 , F01D25/162 , F05D2220/323 , F05D2240/12 , F05D2240/53 , F05D2260/60
Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.
-
公开(公告)号：US20170074517A1
公开(公告)日：2017-03-16
申请号：US15363418
申请日：2016-11-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO
CPC classification number: F23R3/28 , F02C7/222 , F05D2220/32 , F05D2240/35 , F05D2250/36 , F23R3/002 , F23R3/10 , F23R3/283 , F23R3/50
Abstract: A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber.
Abstract translation: 燃气涡轮发动机包括燃烧器。 燃烧器包括形成在内衬和与衬里间隔开的外衬套之间的环形燃烧室。 环形燃料歧管具有沿燃料歧管周向分布的燃料喷嘴，燃料歧管和燃料喷嘴完全位于燃烧室内。
-
公开(公告)号：US20220195888A1
公开(公告)日：2022-06-23
申请号：US17126678
申请日：2020-12-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO , Sandeep Vishal DHALLA
Abstract: A bearing housing cover for a gas turbine engine having an impeller. The bearing housing comprises an annular collar having a flange mountable to an exterior surface of a bearing housing. The bearing housing further comprises an impeller baffle integrated with the annular collar, the impeller baffle having an annular body with a front baffle face positionable adjacent a rear face of the impeller, a rear baffle face having a plurality of stiffening elements extending between the rear baffle face and the annular collar, and a central baffle opening.
-
Patent Agency Ranking
公开(公告)号：US20220082030A1
公开(公告)日：2022-03-17
申请号：US17018409
申请日：2020-09-11
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO
Abstract: A gas turbine engine, has: a case extending circumferentially around a central axis of the gas turbine engine; a boss protruding from the case away from the central axis, the boss defining an internal passage; a tubular member received within the internal passage of the boss and secured to the boss; an annular gap extending all around the tubular member and located between the tubular member and the boss; and a fitting hydraulically connecting a fluid source to the tubular member, the fitting having a portion received within the tubular member and encircled by both of the annular gap and the tubular member, the fitting sealingly engaged to the tubular member.
-
公开(公告)号：US20210262666A1
公开(公告)日：2021-08-26
申请号：US17315495
申请日：2021-05-10
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO , Aleksandar KOJOVIC , Bryan Micheal BOND
Abstract: A fuel supply assembly for a gas turbine engine comprises a plurality of fuel injectors configured for mounting circumferentially to an engine casing of the gas turbine engine and to be serially interconnected. At least one pair of the plurality of the fuel injectors has a first fuel injector including a first manifold adapter having a first outlet defined around a first outlet axis, and a first stem connected to the first manifold adapter at the first outlet and extending longitudinally along a first stem axis; and a second fuel injector including a second manifold adapter having a second outlet defined around a second outlet axis, and a second stem connected to the second manifold adapter at the second outlet, the first and second outlet axes being disposed circumferentially between the first and second stem axes.
-
公开(公告)号：US20210025337A1
公开(公告)日：2021-01-28
申请号：US16671476
申请日：2019-11-01
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO , Aleksandar KOJOVIC , Jeffrey Richard VERHIEL
Abstract: A method of operating a fuel delivery system of an aircraft engine of an aircraft includes operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation, the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft, and no motive power to the aircraft, via the combustion of the trickle flow of fuel. An aircraft gas turbine engine is also described.
-
公开(公告)号：US20180023477A1
公开(公告)日：2018-01-25
申请号：US15705770
申请日：2017-09-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Oleg MORENKO
CPC classification number: F02C7/222 , F02C7/228 , F02C7/232 , F05D2260/231 , F05D2260/602 , F23D2209/30 , Y10S60/904
Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
-
公开(公告)号：US20130327054A1
公开(公告)日：2013-12-12
申请号：US13915990
申请日：2013-06-12
Applicant: Pratt & Whitney Canada Corp.
Inventor： Bhawan B. PATEL , Oleg MORENKO
IPC: F02C7/22
Abstract: A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions.
Abstract translation: 混合燃烧器结合了两种不同的燃料喷射源来在燃烧器中喷射燃料。 燃烧器组合用于在高功率水平和巡航条件期间在第一燃烧区域喷射燃料的旋转燃料抛油环和用于在较低功率水平和起动条件下在第二燃烧区域喷射燃料的一组燃料喷嘴。
-
-
-
-
-
-
-
-
-
Search Results
25
records
(took 0.02 seconds)
