US 2026/0251302 A1Published application

Differential cooling in a small combustor

AssigneeGE Avio S.r.l.

InventorsMirko Pavan, Alessandro Frontani, Claudio Abbondanza, Fabio Turrini

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Abstract

Combustor liners providing differential cooling are disclosed. An example gas turbine engine includes a combustor having combustor volume (V), the combustor configured to burn fuel at a fuel flow rate (FFR) to generate an engine power (Pengine); and a combustor liner having a surface area (SA) including: an inner liner including a plurality of inner liner cooling holes configured to provide cooling to the combustor, the plurality of inner liner cooling holes characterized by an inner liner midcup cooling hole tangential pitch/diameter (TP/DIL, M) between and inclusive of 6 and 16 and an inner liner centerline cooling hole tangential pitch/diameter (TP/DIL, C) between and inclusive 5 and 11, wherein values for a ratio of TP D IL , M ⁢ to ⁢ TP D IL , C are greater than 1.00; an outer liner including a plurality of outer liner cooling holes configured to provide cooling to the combustor.

Claims20

Dependent claims

A gas turbine engine comprising:

a combustor having combustor volume (V), the combustor configured to burn fuel at a fuel flow rate (FFR) to generate an engine power (Pengine);
and
a combustor liner having a surface area (SA) including:
an inner liner including a plurality of inner liner cooling holes to cool the combustor, the plurality of inner liner cooling holes characterized by an inner liner midcup cooling hole tangential pitch/diameter
(
TP
D
IL
,
M
)
between and inclusive of 6 and 16 and an inner liner centerline cooling hole tangential pitch/diameter
(
TP
D
IL
,
C
)
between and inclusive of 5 and 11, wherein values for a ratio of the
TP
D
IL
,
M
to the
TP
D
IL
,
C
are greater than 1.00;
an outer liner including a plurality of outer liner cooling holes to cool the combustor, the plurality of outer liner cooling holes characterized by an outer liner midcup cooling hole tangential pitch/diameter
(
TP
D
OL
,
M
)
between and inclusive of 8 and 19 and an outer liner centerline cooling hole tangential pitch/diameter
(
TP
D
OL
,
C
)
between and inclusive of 5 and 16, wherein values for a ratio of the
T
⁢
P
D
OL
,
M
to the
T
⁢
P
D
OL
,
C
are greater than 1.00;
and
forward nuggets including a plurality of forward nuggets cooling holes to cool the combustor, the plurality of forward nuggets cooling holes characterized by a forward nuggets midcup cooling hole tangential pitch/diameter
(
T
⁢
P
D
FN
,
M
)
between and inclusive of 4 and 7 and a forward nuggets centerline cooling hole tangential pitch/diameter
(
T
⁢
P
D
FN
,
C
)
between and inclusive of 2 and 5, wherein values for a ratio of the
T
⁢
P
D
FN
,
M
to the
T
⁢
P
D
FN
,
C
are greater than 1.00 and wherein
S
⁢
A
V
>
1
⁢
0
.

109 more elements

A combustor comprising:

a combustion chamber having combustor volume (V), the combustor configured to burn fuel at a fuel flow rate (FFR) to generate an engine power (Pengine);
and
a combustor liner having a surface area (SA) including:
an inner liner including a plurality of inner liner cooling holes configured to provide cooling to the combustor, the plurality of inner liner cooling holes characterized by an inner liner midcup cooling hole tangential pitch/diameter
(
T
⁢
P
D
IL
,
M
)
between and inclusive of 6 and 16 and an inner liner centerline cooling hole tangential pitch/diameter
(
T
⁢
P
D
IL
,
C
)
between and inclusive of 5 and 11, wherein values for a ratio of the
T
⁢
P
D
IL
,
M
to the
T
⁢
P
D
IL
,
C
are greater than 1.00;
an outer liner including a plurality of outer liner cooling holes configured to provide cooling to the combustor, the plurality of outer liner cooling holes characterized by an outer liner midcup cooling hole tangential pitch/diameter
(
T
⁢
P
D
OL
,
M
)
between and inclusive of 8 and 19 and an outer liner centerline cooling hole tangential pitch/diameter
(
T
⁢
P
D
OL
,
C
)
between and inclusive of 5 and 16, wherein values for a ratio of the
T
⁢
P
D
OL
,
M
to the
T
⁢
P
D
OL
,
C
are greater than 1.00;
and
forward nuggets including a plurality of forward nuggets cooling holes configured to provide cooling to the combustor, the plurality of forward nuggets cooling holes characterized by a forward nuggets midcup cooling hole tangential pitch/diameter
(
T
⁢
P
D
FN
,
M
)
between and inclusive of 4 and 7 and a forward nuggets centerline cooling hole tangential pitch/diameter
(
T
⁢
P
D
FN
,
C
)
between and inclusive of 2 and 5, wherein values for a ratio of the
T
⁢
P
D
FN
,
M
to the
T
⁢
P
D
FN
,
C
are greater than 1.00, and wherein
S
⁢
A
V
>
1
⁢
0
.

121 more elements

An apparatus for a turbine engine, comprising:

a combustor having combustor volume (V), the combustor configured to burn fuel at a fuel flow rate (FFR) to generate an engine power (Pengine);
and
a combustor liner having a surface area (SA) including:
an inner liner including a plurality of inner liner cooling holes configured to provide cooling to the combustor, the plurality of inner liner cooling holes characterized by an inner liner midcup cooling hole tangential pitch/diameter
(
T
⁢
P
D
IL
,
M
)
between and inclusive of 6 and 16 and an inner liner centerline cooling hole tangential pitch/diameter
(
T
⁢
P
D
IL
,
C
)
between and inclusive of 5 and 11, wherein values for a ratio of the
TP
D
IL
,
M
to the
TP
D
IL
,
C
are greater than 1.00;
an outer liner including a plurality of outer liner cooling holes configured to provide cooling to the combustor, the plurality of outer liner cooling holes characterized by an outer liner midcup cooling hole tangential pitch/diameter
(
TP
D
OL
,
M
)
between and inclusive of 8 and 19 and an outer liner centerline cooling hole tangential pitch/diameter
(
TP
D
OL
,
C
)
between and inclusive of 5 and 16, wherein values for a ratio of the
TP
D
OL
,
M
to the
TP
D
OL
,
C
are greater than 1.00;
and
forward nuggets including a plurality of forward nuggets cooling holes configured to provide cooling to the combustor, the plurality of forward nuggets cooling holes characterized by a forward nuggets midcup cooling hole tangential pitch/diameter
(
TP
D
FN
,
M
)
between and inclusive of 4 and 7 and a forward nuggets centerline cooling hole tangential pitch/diameter
(
TP
D
FN
,
C
)
between and inclusive of 2 and 5, wherein values for a ratio of the
TP
D
FN
,
M
to the
TP
D
FN
,
C
are greater than 1.00, and wherein
SA
V
>
1
⁢
0
.

99 more elements

Dependencies are inferred from the claim text.

Facts

Application: 19/552,732Filed 27 Feb 2026
Priority: IT 10202500000397527 Feb 2025
Published: 27 Aug 2026
Term ends: Not estimatedThe source records don’t support an estimate.

Classification8 codes

F23R 3/002
Continuous combustion chambers using liquid or gaseous fuel: wall structures
F23R 3/06
Air inlet arrangements: arrangement of apertures along the flame tube
F23R 3/50
Characterised by the arrangement or form of the flame tubes or combustion chambers: combustion chambers comprising an annular flame tube within an…
F23R 3/54
Characterised by the arrangement or form of the flame tubes or combustion chambers: reverse-flow combustion chambers