High-speed shaft rating for turbine engines
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 (L CORE ), and the high-pressure compressor has an exit stage diameter (D CORE ). 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 L CORE /D CORE is from 2.1 to 4.3.
1. 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, the engine core including a core forward bearing and a core aft bearing, the core forward bearing being positioned forward of a stage of the high-pressure compressor and the core aft bearing being positioned aft of a stage of the high-pressure turbine, the engine core having a length (L CORE ) defined from the core forward bearing to the core aft bearing, and the high-pressure compressor having an exit stage diameter (D CORE ); 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 a ratio of L CORE /D CORE is greater than or equal to 2.1 and less than
4
.
0
8
(
HSP
X
-
8
)
0.14
wherein HSR is given by:
HSR
=
1
k
*
N
2
R
/
L
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N2 R/L is a redline speed of the high-pressure shaft, and k is a constant with a value of 10 6 inch-RPM, and
wherein HSP X is given by:
HSP
X
=
(
A
ex
)
2
*
P
STD
*
OPR
T
O
FN
T
O
*
(
N
Stg
10
)
2
,
where N Stg is a number of stages in the high-pressure compressor, A EX is an area of an exit stage of the high-pressure compressor, P STD is standard pressure, OPR T/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 FN T/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.
2. The turbomachine engine of claim 1 , wherein a number of stages in the high-pressure compressor is one of eight stages, nine stages, ten stages, or eleven stages.
3. The turbomachine engine of claim 1 , wherein the high-pressure turbine includes one stage or two stages.
4. The turbomachine engine of claim 1 , wherein an exhaust gas temperature of the turbomachine engine at redline speeds of the high-pressure shaft is from 1,063° C. to 1,282° C.
5. The turbomachine engine of claim 1 , wherein HSP X is from 3.8 in 2 to 69.1 in 2 .
6. The turbomachine engine of claim 1 , wherein A EX is from 11 in 2 to 95 in 2 .
7. The turbomachine engine of claim 1 , wherein P STD is approximately 14.7 psi.
8. The turbomachine engine of claim 1 , wherein OPR T/O is from 26.3 to 82.
9. The turbomachine engine of claim 1 , wherein FN T/O is from 12,674 lbf to 107,480 lbf.
10. The turbomachine engine of claim 1 , wherein A EX is given by
A EX =π*(R TIP,EX 2 −R HUB,EX 2 ), where R TIP,EX is a radius of a tip of a high-pressure compressor blade of the exit stage of the high-pressure compressor, and R HUB,EX is a radius of a hub of the high-pressure compressor at the exit stage.
11. The turbomachine engine of claim 10 , wherein R TIP,EX is from 4.73 in. to 15.83 in.
12. The turbomachine engine of claim 10 , wherein R HUB,EX is from 4.31 in. to 14.85 in.
13. A method of operating the turbomachine engine of claim 1 , the method comprising operating the turbomachine engine to generate an engine thrust, a redline speed of the high-pressure shaft being from 10,580 RPM to 35,788 RPM.
14. The turbomachine engine of claim 1 , wherein the stage of the high-pressure compressor is a first stage and the stage of the high-pressure turbine is a last stage such that the core forward bearing is positioned forward of the first stage of the high-pressure compressor and the core aft bearing is positioned aft of the last stage of the high-pressure turbine.
15. 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, the engine core including a core forward bearing and a core aft bearing, the core forward bearing being positioned forward of a stage of the high-pressure compressor and the core aft bearing being positioned aft of a stage of the high-pressure turbine, the engine core having a length (L CORE ) defined from the core forward bearing to the core aft bearing, and the high-pressure compressor having an exit stage diameter (D CORE );
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 a ratio of L CORE /D CORE is greater than or equal to 2.1 and less than
4
.
0
8
(
HSP
X
-
8
)
0.14
wherein HSR is given by:
HSR
=
1
k
*
N
2
R
/
L
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N2 R/L is a redline speed of the high-pressure shaft, and k is a constant with a value of 10 6 inch-RPM, and
wherein HSP X is given by:
HSP
X
=
(
A
ex
)
2
*
P
STD
*
OPR
T
O
FN
T
O
*
(
N
Stg
10
)
2
,
where N Stg is a number of stages in the high-pressure compressor, A EX is an area of an exit stage of the high-pressure compressor, P STD is standard pressure, OPR T/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 FN T/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.
16. The turbomachine engine of claim 15 , wherein the high-pressure shaft is characterized by a second high-pressure shaft rating (HSR LP ) from 0.8 to 1.6, and HSR LP is given by:
HSR
L
P
=
1
k
*
N
1
r
/
1
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N1 r/l is a redline speed of the low-pressure shaft, and k is a constant with a value of 10 6 inch-RPM.
17. The turbomachine engine of claim 15 , wherein N2 R/L is from 10,580 RPM to 35,788 RPM.
18. The turbomachine engine of claim 15 , wherein HSP X is from 3.8 in 2 to 69.1 in 2 .
19. The turbomachine engine of claim 15 , wherein a number of stages in the high-pressure compressor is one of eight stages, nine stages, ten stages, or eleven stages.
20. The turbomachine engine of claim 15 , wherein A EX is from 11 in 2 to 95 in 2 .
21. The turbomachine engine of claim 15 , wherein P STD is approximately 14.7 psi.
22. The turbomachine engine of claim 15 , wherein OPR T/O is from 26.3 to 82.
23. The turbomachine engine of claim 15 , wherein FN T/O is from 12,674 lbf to 107,480 Ibf.
24. 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, the engine core including a core forward bearing and a core aft bearing, the core forward bearing being positioned forward of a stage of the high-pressure compressor and the core aft bearing being positioned aft of a stage of the high-pressure turbine, the engine core having a length (L CORE ) defined from the core forward bearing to the core aft bearing, and the high-pressure compressor having an exit stage diameter (D CORE ), wherein a number of stages in the high-pressure compressor is one of eight stages, nine stages, ten stages, or eleven stages, and the high-pressure turbine includes one stage or two stages; 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 a ratio of L CORE /D CORE is greater than or equal to 2.1 and less than
4
.
0
8
(
HSP
X
-
8
)
0.14
wherein HSR is given by:
HSR
=
1
k
*
N
2
R
/
L
*
D
CORE
*
(
L
CORE
D
CORE
)
2
,
where N2 R/L is a redline speed of the high-pressure shaft, and k is a constant with a value of 10 6 inch-RPM,
wherein HSP X is given by:
HSP
X
=
(
A
ex
)
2
*
P
STD
*
OPR
T
O
FN
T
O
*
(
N
Stg
10
)
2
,
where N Stg is the number of stages in the high-pressure compressor, A EX is an area of an exit stage of the high-pressure compressor, P STD is standard pressure, OPR T/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 FN T/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.
25. The turbomachine engine of claim 24 , wherein N2 R/L is from 10,580 RPM to 35,788 RPM.
26. The turbomachine engine of claim 24 , wherein HSP X is from 3.8 in 2 to 69.1 in 2 .
27. The turbomachine engine of claim 24 , wherein A EX is from 11 in 2 to 95 in 2 .
28. The turbomachine engine of claim 24 , wherein P STD is approximately 14.7 psi.
29. The turbomachine engine of claim 24 , wherein OPR T/O is from 26.3 to 82.
30. The turbomachine engine of claim 24 , wherein FN T/O is from 12,674 lbf to 107,480 lbf.