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61.发明专利
公开(公告)号：SG11201403614VA
公开(公告)日：2014-10-30
申请号：SG11201403614V
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , SUCIU GABRIEL L , KUPRATIS DANIEL BERNARD , ACKERMANN WILLIAM K
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.
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公开(公告)号：SG11201403015WA
公开(公告)日：2014-09-26
申请号：SG11201403015W
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.
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公开(公告)号：SG11201402823TA
公开(公告)日：2014-09-26
申请号：SG11201402823T
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine (20) includes a fan (42), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device (48), such as an epicyclical gear assembly, may be utilized to drive the fan (42) at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). A shaft driven (30) by the turbine section (28) provides an input to the epicyclical gear assembly (48) such that both the turbine section (28) and the fan (42) can rotate at closer to optimal speeds providing increased performance attributes and performance.
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公开(公告)号：CA2854082A1
公开(公告)日：2013-11-14
申请号：CA2854082
申请日：2013-01-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC: F02K3/06
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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公开(公告)号：CA2857351A1
公开(公告)日：2013-10-24
申请号：CA2857351
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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Patent Agency Ranking
公开(公告)号：CA2951916A1
公开(公告)日：2013-08-08
申请号：CA2951916
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.
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公开(公告)号：CA2857360A1
公开(公告)日：2013-08-08
申请号：CA2857360
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC: F02K3/06
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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公开(公告)号：CA2857359A1
公开(公告)日：2013-08-08
申请号：CA2857359
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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公开(公告)号：CA2856723C
公开(公告)日：2021-09-07
申请号：CA2856723
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：CA2916866C
公开(公告)日：2020-02-18
申请号：CA2916866
申请日：2016-01-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , KUPRATIS DANIEL BERNARD
Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.
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