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公开(公告)号：US20120234017A1
公开(公告)日：2012-09-20
申请号：US13483426
申请日：2012-05-30
摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.
摘要翻译： 燃气涡轮发动机包括低压压缩机部分和高压压缩机部分。 低压涡轮机驱动低压压缩机部分。 齿轮装置由低压涡轮机驱动，从而驱动风扇部分。 低压压缩机部分的压力比在大约4-8之间，并且高压压缩机部分的压力比在大约8-15之间。 在单独的特征中，压缩机壳体包括前压缩机壳体部分和后压缩机壳体部分，后压缩机壳体部分比从前压缩机壳体部分的入口壳体更远离轴向。 支撑构件在风扇部分和前压缩机壳体部分之间延伸。
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公开(公告)号：US20130205747A1
公开(公告)日：2013-08-15
申请号：US13370743
申请日：2012-02-10
CPC分类号： F02K3/06 , F02C3/107 , F02C7/04 , F02C7/36 , F05D2210/40 , F05D2250/313 , F05D2250/314 , Y10T29/4932 , Y10T29/49323
摘要： A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.
摘要翻译： 结合有自由涡轮机和风扇的单独的推进单元接收来自多个核心发动机的气体。 核心发动机各自包括压缩机，涡轮机和燃烧部分。 核心发动机组合通过自由涡轮机的气体。 还公开了一种方法。
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公开(公告)号：US20120315130A1
公开(公告)日：2012-12-13
申请号：US13590399
申请日：2012-08-21
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45.
摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过所述低压压缩机部分上的压力比和所述高压压缩机部分之间的压力比的组合提供的总压力比大于约35.跨过高压压缩机部分的压力比介于约 7和15左右，风扇部分的压力比小于或等于1.45。
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公开(公告)号：US08277174B2
公开(公告)日：2012-10-02
申请号：US13418457
申请日：2012-03-13
IPC分类号： F01D25/28
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而高压压缩机部分的压力比为约7至约15。
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公开(公告)号：US08449247B1
公开(公告)日：2013-05-28
申请号：US13590273
申请日：2012-08-21
IPC分类号： F01D1/00
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas a pressure ratio across the fan section being less than or equal to about 1.45.
摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而风扇部分的压力比小于或等于约1.45。
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公开(公告)号：US08337149B1
公开(公告)日：2012-12-25
申请号：US13590399
申请日：2012-08-21
IPC分类号： F01D1/00
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45.
摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过所述低压压缩机部分上的压力比和所述高压压缩机部分之间的压力比的组合提供的总压力比大于约35.跨过高压压缩机部分的压力比介于约 7和15左右，风扇部分的压力比小于或等于1.45。
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公开(公告)号：US08955304B2
公开(公告)日：2015-02-17
申请号：US13370743
申请日：2012-02-10
CPC分类号： F02K3/06 , F02C3/107 , F02C7/04 , F02C7/36 , F05D2210/40 , F05D2250/313 , F05D2250/314 , Y10T29/4932 , Y10T29/49323
摘要： A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.
摘要翻译： 结合有自由涡轮机和风扇的单独的推进单元接收来自多个核心发动机的气体。 核心发动机各自包括压缩机，涡轮机和燃烧部分。 核心发动机组合通过自由涡轮机的气体。 还公开了一种方法。
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公开(公告)号：US08337148B2
公开(公告)日：2012-12-25
申请号：US13483426
申请日：2012-05-30
IPC分类号： F01D25/28
摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.
摘要翻译： 燃气涡轮发动机包括低压压缩机部分和高压压缩机部分。 低压涡轮机驱动低压压缩机部分。 齿轮装置由低压涡轮机驱动，从而驱动风扇部分。 低压压缩机部分的压力比在大约4-8之间，并且高压压缩机部分的压力比在大约8-15之间。 在单独的特征中，压缩机壳体包括前压缩机壳体部分和后压缩机壳体部分，后压缩机壳体部分比从前压缩机壳体部分的入口壳体更远离轴向。 支撑构件在风扇部分和前压缩机壳体部分之间延伸。
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公开(公告)号：US08337147B2
公开(公告)日：2012-12-25
申请号：US13337354
申请日：2011-12-27
IPC分类号： F01D5/06
摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.
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公开(公告)号：US20120171018A1
公开(公告)日：2012-07-05
申请号：US13418457
申请日：2012-03-13
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而高压压缩机部分的压力比为约7至约15。
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