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公开(公告)号：US11098601B2
公开(公告)日：2021-08-24
申请号：US16804641
申请日：2020-02-28
发明人： Christopher David King , David Vickery Parker , John Alan Manteiga , Matthew Brian Surprenant , Megan Lynn Williams , Awot Michael Berhe , Jesse Jacob Ollove
IPC分类号： F01D9/02 , F01D9/04 , F04D29/44 , F04D29/02 , B22F5/10 , B33Y10/00 , B33Y80/00 , B22F5/00 , B22F10/20
摘要： A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.
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公开(公告)号：US20200248571A1
公开(公告)日：2020-08-06
申请号：US16804641
申请日：2020-02-28
发明人： Christopher David King , David Vickery Parker , John Alan Manteiga , Matthew Brian Surprenant , Megan Lynn Williams , Awot Michael Berhe , Jesse Jacob Ollove
IPC分类号： F01D9/02 , F01D9/04 , B22F3/105 , B22F5/00 , B33Y80/00 , B33Y10/00 , B22F5/10 , F04D29/02 , F04D29/44
摘要： A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.
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公开(公告)号：US11674403B2
公开(公告)日：2023-06-13
申请号：US17215539
申请日：2021-03-29
CPC分类号： F01D11/025 , F01D9/04 , F01D11/005 , F01D11/08 , F01D25/246 , F05D2220/32 , F05D2230/60 , F05D2240/11
摘要： A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.
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公开(公告)号：US20220307383A1
公开(公告)日：2022-09-29
申请号：US17215539
申请日：2021-03-29
摘要： A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.
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公开(公告)号：US10718222B2
公开(公告)日：2020-07-21
申请号：US15469708
申请日：2017-03-27
发明人： Christopher David King , David Vickery Parker , John Alan Manteiga , Matthew Brian Surprenant , Megan Lynn Williams , Awot Michael Berhe , Jesse Jacob Ollove
IPC分类号： F02D9/02 , F01D9/02 , B22F3/105 , F01D9/04 , F04D29/44 , F04D29/02 , B22F5/10 , B33Y10/00 , B33Y80/00 , B22F5/00
摘要： A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.
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公开(公告)号：US20180274376A1
公开(公告)日：2018-09-27
申请号：US15469708
申请日：2017-03-27
发明人： Christopher David King , David Vickery Parker , John Alan Manteiga , Matthew Brian Surprenant , Megan Lynn Williams , Awot Michael Berhe , Jesse Jacob Ollove
摘要： A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.
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