-
公开(公告)号：EP0440164A1
公开(公告)日：1991-08-07
申请号：EP91101140.1
申请日：1991-01-29
申请人： HITACHI, LTD.
发明人： Nishijima, Tsunemasa
CPC分类号： F23R3/36 , F02C7/185 , F02C7/2365 , F02C9/40
摘要： A gas turbine system of the type includes an air compressor (1), a turbine (2), a combustor (3), a turbine cooling unit (20), and a fuel oil atomizing unit (21). The turbine cooling unit (20) includes a cooling air passage (7) which communicates an air discharge port (1a) of the air compressor (1) to a cooling air intake (2a, 2b) of the turbine (2). The turbine cooling unit (20) further includes an intercooler (4) provided in the cooling air passage (7), and an air filter (5) provided in the cooling air passage downstream of the intercooler (4). The fuel oil atomizing unit (21) includes an atomization air passage (15) branching from the cooling air passage (7) downstream of the air filter (5) and communicating to an air inlet (14a) of the fuel nozzle (14), and an atomization air compressor (11) disposed in the atomization air passage (15) for compressing atomization air.
摘要翻译： 这种类型的燃气轮机系统包括空气压缩机（1），涡轮机（2），燃烧器（3），涡轮冷却单元（20）和燃料油雾化单元（21）。 涡轮冷却单元（20）包括将空气压缩机（1）的排气口（1a）与涡轮机（2）的冷却空气吸入口（2a，2b）连通的冷却空气通路（7）。 涡轮机冷却单元（20）还包括设置在冷却空气通道（7）中的中间冷却器（4）和设置在中间冷却器（4）下游的冷却空气通道中的空气过滤器（5）。 燃料油雾化单元（21）包括从空气过滤器（5）下游的冷却空气通路（7）分支并与燃料喷嘴（14）的进气口（14a）连通的雾化空气通路（15） 以及设置在雾化空气通路（15）中用于压缩雾化空气的雾化空气压缩机（11）。
-
公开(公告)号：EP0127562B1
公开(公告)日：1990-08-08
申请号：EP84630070.5
申请日：1984-04-27
发明人： Stevens, Leonard W. , Siwik, Williams S. , Moore, William A. , Brown, Wayne M. , Barnard, Andrew A.
CPC分类号： F01D25/183 , F01D11/00 , F01D25/125 , F02C7/185 , F16C19/26 , F16C27/045 , F16C2360/23 , Y02T50/675
-
83.发明公开
公开(公告)号：EP0379880A1
公开(公告)日：1990-08-01
申请号：EP90100305.3
申请日：1990-01-08
CPC分类号： F02C7/185 , F01D5/08 , F01K23/106 , F02C7/14 , Y02E20/16
摘要： In a gas turbine the quantity of cooling air required to cool the turbine (3) is reduced by the evaporative cooling of air bled from the compressor discharge for cooling purposes (34). The evaporative cooling is accomplished by spraying pressurized water (37) into a bleed pipe (23) which diverts the cooling air from the compressor discharge to the turbine (3).
摘要翻译： 在燃气轮机中，为了冷却目的，通过从压缩机排出口排出的空气的蒸发冷却来减少用于冷却涡轮机（3）所需的冷却空气量。 蒸发冷却通过将加压水（37）喷射到排出管（23）中来实现，排放管将冷却空气从压缩机排放口转移到涡轮机（3）。
-
公开(公告)号：EP4431385A1
公开(公告)日：2024-09-18
申请号：EP24164292.5
申请日：2024-03-18
发明人： DUROCHER, Eric S.
CPC分类号： B64D33/08 , F28D7/0025 , F28D7/0083 , F28D9/0081 , F28D2021/002120130101 , F28D2021/002620130101 , F28F1/40 , F28F9/0265 , F28F9/028 , F02C7/12 , B64C11/00 , F02C7/14 , F02C7/185 , B64D33/10
摘要： A heat exchanger assembly for an aircraft includes a housing (92), a heat exchanger (96), and a nozzle (152). The housing (92) includes an inner flow path wall (100) and an outer flow path wall (102). The inner flow path wall (100) and the outer flow path wall (102) form an air inlet (106), an air outlet (108), and a venturi channel (134). The heat exchanger (96) includes a heat exchanger body (194), a heat transfer plenum (212), a plenum inlet (214), and a plenum outlet (216). The heat exchanger body (194) is disposed downstream of the venturi channel (134) within the air flow path (110). The heat exchanger (96) is configured to direct a fluid from through the heat transfer plenum (212) from the plenum inlet (214) to the plenum outlet (216). The nozzle includes (152) a nozzle housing (158) disposed within the air flow path (110). The nozzle housing (158) forms a nozzle inlet (176) and a nozzle outlet (178). The nozzle outlet (178) is disposed within the venturi channel (134).
-
公开(公告)号：EP3379036B1
公开(公告)日：2024-09-04
申请号：EP17162453.9
申请日：2017-03-22
CPC分类号： F01D11/003 , F01D11/24 , F02C6/08 , F02C7/185 , F05D2260/21320130101
-
公开(公告)号：EP2374995B1
公开(公告)日：2018-12-26
申请号：EP11161124.0
申请日：2011-04-05
CPC分类号： F01D5/081 , F01D9/065 , F02C6/08 , F02C7/143 , F02C7/185 , F04D29/321 , F04D29/5826 , F04D29/584 , F05D2220/3219 , F05D2260/205 , F05D2260/213
摘要： A gas turbine engine (10) includes a turbine (24) and a high pressure compressor (18). The high pressure compressor (18) includes a last stage having a last stage compressor blade (34a) and a last stage vane (36a). The gas turbine engine (10) includes a first flow path through which bleed air flows to the turbine (24) and a second flow path through which air from the last stage of the high pressure compressor (18) flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger (50) to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor (18) to cool the high pressure compressor (18).
-
公开(公告)号：EP3121411B1
公开(公告)日：2018-12-12
申请号：EP16180657.5
申请日：2016-07-21
CPC分类号： F02C6/08 , F02C7/185 , F02C9/18 , F05D2220/3219 , F05D2260/211 , F05D2260/213 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.
-
公开(公告)号：EP3246545B1
公开(公告)日：2018-12-05
申请号：EP17169591.9
申请日：2017-05-04
发明人： Sweeney, Patrick C. , Heister, Stephen Douglas , Hunt, Steven Alan , Scalo, Carlo , Migliorino, Marto Tindaro
CPC分类号： F02C7/185 , F02C7/224 , F05D2260/213 , Y02T50/676
摘要： A gas turbine engine includes devices, systems, and methods for design and operation of stabilizing heat exchangers for gas turbine engines in consideration of near supercritical fuel flow conditions.
-
公开(公告)号：EP2580447B1
公开(公告)日：2018-11-14
申请号：EP11723816.2
申请日：2011-05-24
申请人： Siemens Energy, Inc.
CPC分类号： F02C7/185 , F02C7/18 , F02C7/224 , F05D2240/12 , F05D2260/205 , F05D2260/213 , F05D2260/22141 , F05D2270/303
摘要： A cooling system for turbine engines for controlling cooling of rotor cooling air and heating of fuel gas is disclosed. The cooling system may be formed from a housing formed from a main plenum, a rotor air cooler positioned at least partially in the main plenum and a fuel gas heater positioned at least partially in the main plenum downstream from rotor air cooler. The cooling system may include a by-pass plenum for returning used cooling air back to a region upstream of the rotor air cooler. An exhaust fluid control device may control fluid flow out of the first exhaust opening at the second end of the main plenum, and a by-pass fluid control device may control fluid flow into the by-pass inlet opening of the by-pass plenum. The control devices and a fan may control circulation of cooling fluids through the main plenum.
-
公开(公告)号：EP3385652A1
公开(公告)日：2018-10-10
申请号：EP18165672.9
申请日：2018-04-04
CPC分类号： B21D53/06 , B23P15/26 , F02C6/08 , F02C7/143 , F02C7/18 , F02C7/185 , F02C9/18 , F05D2220/30 , F05D2230/31 , F05D2260/213 , F28D2021/0021 , F28F1/022 , F28F1/04 , F28F1/08 , F28F1/12 , F28F1/124 , F28F1/16 , F28F21/087 , Y02T50/675
摘要： An aspect of a method of forming a heat exchanger 50, 150 includes providing 1000 a metal body 60, 160, removing material from the metal body 60, 160 to partially create 1002 a set of cooling passages 70, 170, filling 1004 the partially created set of cooling passages 70, 170 with sacrificial material 76, forming 1006 a remainder of the set of cooling passages 70, 170 such that a set of fully formed cooling passages 70, 170 for the heat exchanger 50, 150 are defined, and removing 1008 the sacrificial material 76 from the cooling passages 70, 170.
-
-
-
-
-
-
-
-
-
搜索结果
484 条记录 (耗时 0.014 秒)
