US 2026/0309105 A1Published application

Radius ratio high-speed shaft rating for turbine engines

AssigneeGeneral Electric Company

InventorsBhaskar Nanda Mondal, Narayanan Payyoor, Pranav Kamat

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Abstract

A turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). A high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine. The high-pressure shaft is characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE/DCORE is from 2.1 to 4.3.

Claims30

Dependent claims

A turbomachine engine comprising:

an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine;
and
a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine, the high-pressure shaft characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and wherein the high-pressure shaft is further characterized by a radius ratio high-speed shaft rating (HSPRR) that is greater than or equal to 9.1 and less than at least one of
MAX
⁡
(
77
-
2.6
*
(
HSP
X
)
,
27
-
0.2
*
(
HSP
X
)
)
⁢
or
⁢
165
HSP
X
0.6
,
wherein HSR is given by:
HSR
=
1
k
*
N
⁢
2
R
L
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N2R/L is a redline speed of the high-pressure shaft, LCORE is a length of the engine core, DCORE is a diameter of the engine core, and k is a constant with a value of 106 inch-RPM,
HSPRR is given by:
HSP
RR
=
(
L
core
D
core
*
T
⁢
25
T
O
T
STD
)
2
R
HUB
,
IN
R
TIP
,
IN
*
R
TIP
,
EX
R
TIP
,
IN
,
where T25T/O is a temperature at an inlet of the high-pressure compressor, TSTD is standard day temperature and is equal to 518.67°R, RHUB,IN is a radius of a hub at the inlet of the high-pressure compressor, RTIP,IN is a radius of a tip of a high-pressure compressor blade at the inlet of the high-pressure compressor, and RTIP,EX is a radius of a tip of a high-pressure compressor blade at an exit stage of the high-pressure compressor, and
HSPX is given by:
HSP
X
=
(
A
ex
)
2
*
P
STD
*
OPR
T
O
FN
T
O
*
(
N
Stg
10
)
2
,
where NStg is a number of stages in the high-pressure compressor, AEX is an area of an exit stage of the high-pressure compressor, PSTD is standard pressure, OPRT/O is an overall pressure ratio of the turbomachine engine at takeoff flight conditions corresponding to a maximum thrust rating for an engine core configuration, and FNT/O is a sea-level static thrust of the turbomachine engine at takeoff flight conditions corresponding to the maximum thrust rating for the engine core configuration.

119 more elements

A turbomachine engine comprising:

an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine;
a power turbine in flow communication with the high-pressure turbine;
a low-pressure shaft coupled to the power turbine;
and
a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine, the high-pressure shaft characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and wherein the high-pressure shaft is further characterized by a radius ratio high-speed shaft rating (HSPRR) that is greater than or equal to 9.1 and less than at least one of
MAX
⁡
(
77
-
2.6
*
(
HSP
X
)
,
27
-
0.2
*
(
HSP
X
)
)
⁢
or
⁢
165
HSP
X
0.6
,
wherein HSR is given by:
HSR
=
1
k
*
N
⁢
2
R
L
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N2R/L is a redline speed of the high-pressure shaft, LCORE is a length of the engine core, DCORE is a diameter of the engine core, and k is a constant with a value of 106 inch-RPM,
HSPRR is given by:
HSP
RR
=
(
L
core
D
core
*
T
⁢
25
T
O
T
STD
)
2
R
HUB
,
IN
R
TIP
,
IN
*
R
TIP
,
EX
R
TIP
,
IN
,
where T25T/O is a temperature at an inlet of the high-pressure compressor, TSTD is standard day temperature and is equal to 518.67°R, RHUB,IN is a radius of a hub at the inlet of the high-pressure compressor, RTIP,IN is a radius of a tip of a high-pressure compressor blade at the inlet of the high-pressure compressor, and RTIP,EX is a radius of a tip of a high-pressure compressor blade at an exit stage of the high-pressure compressor, and
HSPX is given by:
HSP
X
=
(
A
ex
)
2
*
P
STD
*
OPR
T
O
FN
T
O
*
(
N
Stg
10
)
2
,
where NStg is a number of stages in the high-pressure compressor, AEX is an area of an exit stage of the high-pressure compressor, PSTD is standard pressure, OPRT/O is an overall pressure ratio of the turbomachine engine at takeoff flight conditions corresponding to a maximum thrust rating for an engine core configuration, and FNT/O is a sea-level static thrust of the turbomachine engine at takeoff flight conditions corresponding to the maximum thrust rating for the engine core configuration.

121 more elements

Dependencies are inferred from the claim text.

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Abstract

A turbomachine engine comprising:

an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine;
and
a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine, the high-pressure shaft characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and wherein the high-pressure shaft is further characterized by a radius ratio high-speed shaft rating (HSPRR) that is greater than or equal to 9.1 and less than at least one of
MAX
⁡
(
77
-
2.6
*
(
HSP
X
)
,
27
-
0.2
*
(
HSP
X
)
)
⁢
or
⁢
165
HSP
X
0.6
,
wherein HSR is given by:
HSR
=
1
k
*
N
⁢
2
R
L
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N2R/L is a redline speed of the high-pressure shaft, LCORE is a length of the engine core, DCORE is a diameter of the engine core, and k is a constant with a value of 106 inch-RPM,
HSPRR is given by:
HSP
RR
=
(
L
core
D
core
*
T
⁢
25
T
O
T
STD
)
2
R
HUB
,
IN
R
TIP
,
IN
*
R
TIP
,
EX
R
TIP
,
IN
,
where T25T/O is a temperature at an inlet of the high-pressure compressor, TSTD is standard day temperature and is equal to 518.67°R, RHUB,IN is a radius of a hub at the inlet of the high-pressure compressor, RTIP,IN is a radius of a tip of a high-pressure compressor blade at the inlet of the high-pressure compressor, and RTIP,EX is a radius of a tip of a high-pressure compressor blade at an exit stage of the high-pressure compressor, and
HSPX is given by:
HSP
X
=
(
A
ex
)
2
*
P
STD
*
OPR
T
O
FN
T
O
*
(
N
Stg
10
)
2
,
where NStg is a number of stages in the high-pressure compressor, AEX is an area of an exit stage of the high-pressure compressor, PSTD is standard pressure, OPRT/O is an overall pressure ratio of the turbomachine engine at takeoff flight conditions corresponding to a maximum thrust rating for an engine core configuration, and FNT/O is a sea-level static thrust of the turbomachine engine at takeoff flight conditions corresponding to the maximum thrust rating for the engine core configuration.

119 more elements