U.S. patent number 3,672,162 [Application Number 05/110,449] was granted by the patent office on 1972-06-27 for combustion chamber assembly for a gas turbine engine.
This patent grant is currently assigned to Avco Corporation. Invention is credited to Brian W. Doyle, Joseph Rygelis, Ervin J. Sweet.
United States Patent |
3,672,162 |
Rygelis , et al. |
June 27, 1972 |
COMBUSTION CHAMBER ASSEMBLY FOR A GAS TURBINE ENGINE
Abstract
A combustion chamber liner is comprised of two telescoping
sections, the leading edge of the downstream section overlapping
the trailing edge of the upstream section. The end of the upstream
section is provided with a plurality of peripherally spaced bosses.
The outer peripheral surface of each of the bosses is grooved to
accept the complementary depressed ring in the end of the larger
downstream section. When cool, the dimensions of the upstream and
downstream sections are such that there is a loose connection
between the sections. However, the upstream section is heated more
than the downstream section and causes its expansion to provide a
tight fit.
Inventors: |
Rygelis; Joseph (Monroe,
CT), Sweet; Ervin J. (Trumbull, CT), Doyle; Brian W.
(Shelton, CT) |
Assignee: |
Avco Corporation (Stratford,
CT)
|
Family
ID: |
22333071 |
Appl.
No.: |
05/110,449 |
Filed: |
January 28, 1971 |
Current U.S.
Class: |
60/800; 285/187;
60/757; 285/319; 285/921 |
Current CPC
Class: |
F23R
3/08 (20130101); Y10S 285/921 (20130101) |
Current International
Class: |
F23R
3/04 (20060101); F23R 3/08 (20060101); F02c
003/00 () |
Field of
Search: |
;60/39.65,39.32,39.66 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Wyche; Benjamin W.
Assistant Examiner: Olsen; Warren
Claims
We claim:
1. A combustor having upstream and downstream radially spaced
telescoping sections, an end of said downstream section overlapping
an end of said upstream section;
a plurality of peripherally spaced bosses on the outer surface of
said upstream section at said end thereof;
a groove in each of said bosses, said grooves being peripherally
aligned;
a peripheral ring on the inner surface of said downstream section
at the end thereof, said ring being complementary to said
groove;
the space between said bosses providing cooling air inlets to said
combustor, said ring being dimensioned to sit loosely in said
groove without sufficient clearance to permit separation of the
sections under normal cool non-operating conditions, said fit
becoming tight under normal hot operating conditions due to the
difference in expansion of said sections.
2. The invention as defined in claim 1, and a plurality of
longitudinal slots through the end of said downstream section to
permit the upstream and downstream section to be snap fitted.
3. The invention as defined in claim 1 wherein said ring is
integral with said downstream section.
4. A combustor having upstream and downstream radially spaced
telescoping sections, and end of said downstream section
overlapping an end of said upstream section, the outer surface of
the end of the upstream section being surrounded by the inner
surface of the end of the downstream section;
a plurality of peripherally spaced bosses on one of said
surfaces;
a groove in each of said bosses, said grooves being peripherally
aligned;
a peripheral ring on said other surface, said ring being
complementary to said groove;
the space between said bosses providing cooling air inlets to said
combustor, said ring being dimensioned to fit loosely in said
groove without sufficient clearance to permit separation of the
sections under normal cool non-operating conditions, said fit
becoming tight under normal hot operating conditions due to the
difference in expansion of said sections.
5. The invention as defined in claim 4, and a plurality of
longitudinal slots through said other one of said surfaces to
permit said sections to be snap fitted.
6. The invention as defined in claim 4 wherein said ring is
integral with said other surface.
7. The invention as defined in claim 4 wherein said telescoping
sections form an expansion area immediately downstream of said
bosses.
Description
BACKGROUND OF THE INVENTION
The combustor for the conventional gas turbine engine is often made
of telescoped generally cylindrical combustor sections. A common
method for manufacturing these combustors is to telescope a number
of sections and spotweld them together at circumferentially spaced
points along their overlapping edges. The assembly of such
telescoping sections is often difficult and frequently requires
complex joints for providing a firm construction while at the same
time admitting cooling air. Moreover, the telescoping sections are
subjected to different temperatures, and hence the stresses
introduced by relative expansion of the sections can cause fatigue
leading to premature failure of the metals.
The combustion chamber of this invention provides a simple and
efficient means for supporting the telescoping sections of the
combustor while at the same time permitting expansion of the
combustor sections. Briefly stated, the overlapping sections of the
combustor are interconnected by a snap fit between the grooves in
the elevated bosses in one section and a circumferential ring
depressed into the other section, the space between the bosses
providing for the admission of coolant air into the combustor
chamber. The dimensions of the overlapping sections are chosen so
that the fit between the sections when cool is loose. When heated,
the upstream section is subjected to greater heat and its expansion
with respect to the downstream section produces a rigid fit without
introducing stresses sufficient to cause fatigue in the metals.
THE DRAWINGS
FIG. 1 is an axial cross section of a combustor liner assembled in
accordance with this invention;
FIG. 2 is a section taken through the line 2--2 in FIG. 1; and
FIG. 3 is an enlargement showing the detail of the bosses and
ring.
DESCRIPTION OF THE ILLUSTRATED EMBODIMENT
FIG. 1 shows two overlapping sections 10 and 12 of a combustor
suitable for use in a gas turbine engine. While only two sections
are shown, it will be understood that the combustor may comprise
several additional sections and that the sections in practice have
other configurations; that is to say, the walls may have more
complex shapes, may include perforations for the admission of
cooling air, and may be grooved in the direction of gas flow.
Compressed air is delivered to the combustor from a compressor (not
shown) in the direction of the arrow 14. The trailing edge of the
upstream section 10 is provided with a plurality of peripherally
spaced bosses 16, all of which have peripherally aligned grooves
18.
The end of the downstream section 12 is provided with a peripheral
ring 20 depressed into the end of the section. The ring 20 has a
configuration which is generally complementary to the groove 18. In
addition, the downstream section is provided with longitudinal
slots 22 at the grooved end, permitting the end to snap on to the
bosses 16.
The dimensions of the bosses 16 and the grooves 20 are selected so
that there is a loose fit between the sections when snapped
together in a normal cool non-operating condition. Because of the
direction of flow of the cooling air, the upstream section is
subjected to more heat than the downstream section, and therefore,
the upstream section expands more than the downstream section. When
fully heated to operating temperature a tight fit results if the
dimensions have been properly selected.
While a slotted downstream section permits a snap on connection, it
will be understood that is is also possible to provide a joint
between the two sections without the use of the longitudinal slots.
Under these circumstances it would be necessary to apply heat to
the downstream section to expand it sufficiently to permit its
fitting onto the bosses 16. The heat of operation will cause the
tightening of the section in the same manner as with the slotted
configuration.
While the upstream section of the illustrated embodiment is shown
as including the bosses and the downstream section is provided with
the ring, it is clear that these elements can be reversed so that
the bosses are positioned on the inner surface of the downstream
section. In either case, the area of the combustor between the
overlapping sections and immediately downstream of the bosses
provides an expansion area for the compressed air. This tends to
improve the performance of the combustor and is one of the
advantages of the invention.
CONCLUSION
In summary, Applicants have devised a simple joint for securing the
overlapping sections of a combustion chamber. In operation the
joint is rigid, it produces no excessive stresses on the metals,
and at the same time it permits the in-flow of cooling air to the
combustion chamber.
* * * * *