U.S. patent application number 13/721803 was filed with the patent office on 2014-09-25 for compressor casing assembly providing access to compressor blade sealing assembly.
This patent application is currently assigned to General Electric Company. The applicant listed for this patent is General Electric Company. Invention is credited to Sanji Ekanayake, Joseph P. Rizzo, Alston Ilford Scipio.
Application Number | 20140286766 13/721803 |
Document ID | / |
Family ID | 49766953 |
Filed Date | 2014-09-25 |
United States Patent
Application |
20140286766 |
Kind Code |
A1 |
Ekanayake; Sanji ; et
al. |
September 25, 2014 |
Compressor Casing Assembly Providing Access To Compressor Blade
Sealing Assembly
Abstract
A compressor casing assembly includes a forward compressor
casing, a removable cover and a seal assembly. A midcompressor
casing is provided with a cavity adapted to receive the seal
assembly, and a cover groove adapted to receive the removable
cover. The removable cover secures the seal assembly.
Inventors: |
Ekanayake; Sanji; (Mableton,
GA) ; Scipio; Alston Ilford; (Mableton, GA) ;
Rizzo; Joseph P.; (Simpsonville, SC) |
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Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company; |
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|
US |
|
|
Assignee: |
General Electric Company
Schenectady
NY
|
Family ID: |
49766953 |
Appl. No.: |
13/721803 |
Filed: |
December 20, 2012 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
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13610269 |
Sep 11, 2012 |
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13721803 |
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Current U.S.
Class: |
415/201 |
Current CPC
Class: |
F01D 11/24 20130101;
F01D 11/08 20130101; F01D 11/14 20130101; F04D 29/60 20130101; F01D
25/24 20130101 |
Class at
Publication: |
415/201 |
International
Class: |
F01D 25/24 20060101
F01D025/24; F04D 29/60 20060101 F04D029/60 |
Claims
1. A compressor casing assembly, comprising: a forward compressor
casing; a removable cover a seal assembly a midcompressor casing
having a cavity adapted to receive the seal assembly, and a cover
groove adapted to receive the removable cover; and wherein the
removable cover secures the seal assembly.
2. The compressor casing assembly of claim 1, wherein the removable
cover is removably fastened to the midcompressor casing.
3. The compressor casing assembly of claim 1, wherein the cavity is
configured to prevent movement of the seal assembly in a radial
direction.
4. The compressor casing assembly of claim 1, wherein the seal
assembly comprises a T-shaped member having a first projection and
a second projection, and wherein the cavity has a notch adapted to
receive the second projection.
5. The compressor casing assembly of claim 4, a removable cover has
a cover notch adapted to receive first projection.
6. The compressor casing assembly of claim 1, wherein the removable
cover comprises an arcuate member.
7. The compressor casing assembly of claim 1, wherein the forward
compressor casing is disposed in contact with the removable
cover.
8. A turbine engine, comprising: a midcompressor casing having a
face surface and an inner surface, the midcompressor casing having
a cavity formed on the inner surface and a groove formed on the
face surface; a plurality of arcuate seal segments configured to be
inserted into the cavity; a removable cover disposed in contact
with at least one of the plurality of arcuate seal segments and
being removably secured to the midcompressor casing.
9. The turbine engine of claim 8, wherein each of the plurality of
arcuate seal segments comprises a sealing surface extending a full
circumferential length along each of the plurality of arcuate seal
segments.
10. The turbine engine of claim 9, wherein the sealing surface
comprises one of an abradable seal surface, a honeycomb seal
surface, and a brush seal surface.
11. The turbine engine of claim 8 wherein the removable cover is an
arcuate member.
12. The turbine engine of claim 8 further comprising a forward
compressor casing disposed adjacent to the removable cover.
13. An assembly, comprising: a midcompressor casing having a face
surface and an inner surface, the inner surface having a cavity and
the face surface having a cover groove; a plurality of arcuate seal
segments configured to be inserted into the cavity; and a removable
cover adapted to be inserted into the cover groove, the removable
cover disposed in contact with at least some of the plurality of
arcuate seal segments and secured to the midcompressor casing.
14. The assembly of claim 13, wherein the removable cover is
removably fastened to the midcompressor casing.
15. The assembly of claim 13 wherein the cavity is configured to
prevent movement of the plurality of arcuate seal segments in a
radial direction.
16. The assembly of claim 13 wherein the removable cover is an
arcuate member having a peripheral length that is longer than a
peripheral length of each of the plurality of arcuate seal
segments.
17. The assembly of claim 13 wherein each of the plurality of
arcuate seal segments comprises a sealing surface extending a full
circumferential length along each of the plurality of arcuate seal
segments, the sealing surface extending a distance above and below
a radially inner surface of the midcompressor casing when each of
the plurality of arcuate seal segments is coupled the midcompressor
casing.
18. The assembly of claim 17 wherein the sealing surface comprises
one of an abradable seal surface, a honeycomb seal surface, and a
brush seal surface.
19. The assembly of claim 13 wherein each of the plurality of
arcuate seal segments comprises a T-shaped member having a first
projection that engages a notch formed on the midcompressor casing
and a cover groove formed on the removable cover.
20. The assembly of claim 13 further comprising a forward
compressor casing disposed in contact with removable cover.
Description
CROSS-REFERENCE TO RELATED APPLICATION
[0001] This application is a continuation-in-part of copending
application Ser. No. 13/610,269 titled "REPLACEABLE SEALS FOR
TURBINE ENGINE COMPONENTS AND METHODS FOR INSTALLING THE SAME"
filed on Sep. 11, 2012, which is hereby incorporated by
reference.
TECHNICAL FIELD
[0002] The subject matter disclosed herein relates generally to
turbine engine components and, more specifically, to compressor
casing assemblies.
BACKGROUND
[0003] Turbine engines operate according to well-known principles
wherein an incoming stream of atmospheric air flows through the
engine along an axially-extending flow path. In at least some
turbine engines, at least a portion of the incoming air is
compressed in a compressor section of the engine and is then mixed
with fuel and ignited in a combustor section to produce a
high-energy, high-temperature exhaust gas stream. The hot gas
stream exits the combustor and is channeled through a turbine
section that extracts energy from the exhaust stream to power the
compressor and to provide useful work, such as powering an aircraft
in flight or producing electricity.
[0004] In the compressor and turbine sections of known gas turbine
engines, blades rotate about the center axis of the engine. Engine
efficiency depends at least partially on minimizing leakage in an
effort to maximize interaction between the gas stream and blades.
Within known turbines, one source of inefficiency is leakage of gas
past the tips of the blades and between the blade tips and the
surrounding engine casing. Although a close tolerance fit may be
obtained by fabricating the mating parts to a close tolerance
range, such a fabrication process is costly and time-consuming, and
may result in rubbing an inner surface of the casing.
[0005] As such, to increase engine efficiency, at least some
turbines use a sealing element along the inner surface of the
casing, to reduce leakage between the blade tips and the casing.
Various sealing techniques have been used. Generally, known sealing
elements lose effectiveness over time and may require
replacement.
[0006] However, in order to replace known sealing elements, the
engine casing and the rotor must be removed from the engine to
provide workers access to the sealing elements. Such a process
significantly increases the maintenance costs and may cause a
prolonged duration in engine outages.
BRIEF DESCRIPTION OF THE INVENTION
[0007] The disclosure provides a solution to the problem of having
to remove the midcompressor casing of a turbine engine in order to
access the zero stage seal assembly of the compressor.
[0008] In accordance with one exemplary non-limiting embodiment,
the invention relates to a compressor casing assembly. The
compressor casing assembly includes a forward compressor casing; a
removable cover and a seal assembly. The compressor casing assembly
also includes a midcompressor casing having a cavity adapted to
receive the seal assembly, and a cover groove adapted to receive a
removable cover that secures the seal assembly.
[0009] In another embodiment, a turbine engine is provided having a
midcompressor casing having a face surface and an inner surface,
the compressor casing having a cavity formed on the inner surface
and a groove formed on the face surface. The turbine engine also
includes a plurality of arcuate seal segments configured to be
inserted into the cavity, and a removable cover disposed in contact
with the arcuate seal segments and being removably secured to the
midcompressor casing.
[0010] In another embodiment, an assembly is provided having a
midcompressor casing having a face surface and an inner surface,
the inner surface having a cavity and the face surface having a
cover groove. The assembly includes a plurality of arcuate seal
segments configured to be inserted into the cavity. The assembly
also includes a removable cover adapted to be inserted into the
cover groove, the removable cover is disposed in contact with at
least some of the plurality of arcuate seal segments and secured to
the compressor casing.
[0011] Other features and advantages of the present invention will
be apparent from the following more detailed description of the
preferred embodiment, taken in conjunction with the accompanying
drawings which illustrate, by way of example, the principles of
certain aspects of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] FIG. 1 is a cross-sectional view of a turbine engine taken
along a longitudinal axis of the turbine engine.
[0013] FIG. 2 is a detailed cross sectional view of an embodiment
of the casing assembly.
[0014] FIG. 3 is a cross-sectional view of an embodiment of a seal
assembly.
[0015] FIG. 4 is a cross-sectional view of an embodiment of a
midcompressor casing.
[0016] FIG. 5 is a cross-sectional view of an embodiment of a
removable cover.
[0017] FIG. 6 is an axial view of the first compressor stage and
illustrates an exemplary seal assembly.
DETAILED DESCRIPTION OF THE INVENTION
[0018] The embodiments disclosed herein provide for easy access to
a zero stage seal assembly without removal of a midcompressor
casing. This is accomplished with a removable cover that is secured
to the midcompressor casing that serves to hold the zero stage seal
assembly in place. Removal of the removable cover provides access
to the zero stage seal assembly.
[0019] FIG. 1 is a cross-sectional view of a turbine engine 11
taken through a longitudinal axis 12 extending through the turbine
engine 11. In the exemplary embodiment, turbine engine 11 also
includes a compressor 13 having a plurality of rotor blades 15 that
are circumferentially spaced and that extend radially outward
towards a midcompressor casing 17 from a rotor wheel 19 which
collectively form the rotor shaft. Stator vanes 20 are positioned
adjacent to each set of rotor blades 15, and in combination form
one of a plurality of stages 21. Stator vanes 20 are securely
coupled to midcompressor casing 17 and extend radially inward to
interface with rotor wheel 19. Each of the plurality of stages 21
directs a flow of compressed air through compressor 13. Rotor
blades 15 are circumscribed by midcompressor casing 17, such that
an annular gap (not shown in FIG. 1) is defined between
midcompressor casing 17 and a rotor blade tip 23 of each of the
rotor blades 15.
[0020] Each gap is sized to facilitate minimizing a quantity of
compressed air that bypasses the rotor blades 15. Specifically, in
the exemplary embodiment, a seal assembly 25 is used between
midcompressor casing 17 and rotor 26 to substantially seal the gap
defined therebetween. Specifically, seal assembly 25 facilitates
reducing bypass flow of compressed air between midcompressor casing
17 and rotor blade tip 23. In the exemplary embodiment, compressor
13 includes eighteen separate stages 21. Alternatively, seal
assembly 25 as described herein may be employed in any suitable
type of compressor with any number of stages. An inlet guide vane
(IGV 27) is positioned upstream form the rotor blades 15. IGV 27
directs the airflow onto the rotor blades 15.
[0021] During operation, air flows into turbine engine 11 through
intake 16 and towards compressor 13. Stator vanes 20 direct the
compressed air towards rotor blades 15. The compressed air applies
motive forces to rotor blades 15 to compress the air flowing
through each of the plurality of stages 21.
[0022] Illustrated in FIG. 2 is an enlarged view of the detail area
29 shown in FIG. 1 illustrating a casing assembly 31. Casing
assembly 31 is disposed adjacent to IGV 27, zero stage rotor 35 and
zero stage stator 37. Zero stage seal assembly 39 is disposed
adjacent to zero stage rotor 35. Casing assembly 31 includes a
midcompressor casing 17 and a forward compressor casing 22.
Midcompressor casing 17 and forward compressor casing 22 are
fastened by means of casing fastener(s) 41. Casing assembly 31 also
includes a removable cover 43 disposed between the forward
compressor casing 22 and the midcompressor casing 17. Removable
cover 43 is an arcuate member (has arcuate shape). Casing assembly
31 also includes a zero stage seal assembly 39 that is secured to
midcompressor casing 17 by removable cover 43. Zero stage seal
assembly 39 includes a removable seal support 45 and a seal 47.
[0023] Removable cover 43 may be fastened to midcompressor casing
17 by means of cover fasteners 49. The removable seal support and
seal are joined by means of seal fasteners 51.
[0024] FIG. 3 is a detailed cross section of zero stage seal
assembly 39. Zero stage seal assembly 39 includes a t-shaped member
63 having a base 65, a top surface 66, a first projection 67, a
side surface 68 and a second projection 69. Seal 47 may include an
abradable seal surface, a honeycomb seal surface, a brush seal
surface, and/or any seal surface that enables the zero stage seal
assembly 39 to function as described herein. Seal surface 70 may be
thermally sprayed, brushed, and/or baked, and may be fabricated
from a metallic material, a ceramic material, or any other material
that enables seal surface 70 to function as described herein. Seal
surface 70 may include a plurality of bristles formed from a
metallic or non-metallic material, such as ceramics, carbon fiber,
and/or silica.
[0025] FIG. 4 is a cross section of a portion of the midcompressor
casing 17. The midcompressor casing 17 has a face surface 71, a
horizontal inner surface 73 and a vertical inner surface 75.
Midcompressor casing 17 has a notch 77 configured to engage the
first projection 67 of the zero stage seal assembly 39. The
midcompressor casing 17 is additionally provided with a cover
groove 79 configured to engage the removable cover 43.
[0026] FIG. 5 is a cross-section of the removable cover 43.
Removable cover 43 is provided with a cover notch 81 configured to
engage second projection 69 of the zero stage seal assembly 39.
[0027] When installed, forward compressor casing 22 is fastened to
midcompressor casing 17 and the zero stage seal assembly 39 is
disposed in the cavity 82 formed by horizontal inner surface 73,
vertical inner surface 75 and notch 77. The zero stage seal
assembly 39 is positioned so that first projection 67 of the zero
stage seal assembly 39 is disposed in the notch 77 in the
midcompressor casing 17. This configuration prevents movement of
the zero stage seal assembly 39 in a radial direction. The zero
stage seal assembly 39 is secured in place with the removable cover
43. Cover notch 81 is configured to engage second projection 69 of
the zero stage seal assembly 39. Forward compressor casing 22 and
midcompressor casing 17 maintain the removable cover 43 in place
during operation.
[0028] FIG. 6 is an axial view along longitudinal axis 12 of the
first of the plurality of stages 21 looking aft with the forward
compressor casing 22 removed. The midcompressor casing 17 may
include a casing upper half 87 and a casing lower half 89. The
removable seal support 45 may include a plurality of arcuate seal
segments 90 such as first upper seal segment 91, first lower seal
segment 93, second lower seal segment 95, and second upper seal
segment 97 that are removably coupled to an inner surface of
midcompressor casing 17. Each of the plurality of arcuate seal
segments 90 include a sealing surface extending a full
circumferential length along each of the plurality of arcuate seal
segments 90. The sealing surface extends a distance above and below
a radially inner surface of the midcompressor casing 17 when each
of the plurality of arcuate seal segments 90 is coupled the
midcompressor casing 17. In the exemplary embodiment, the seal
assembly 25 includes four seal segment, but may include any number
of seal segments that enables seal assembly 25 to function as
described herein. The removable cover 43 is fastened to the
midcompressor casing 17 with cover fasteners 49. The removable
cover 43 has a longer peripheral length than any one of the arcuate
seal segments 90 (e.g. first upper seal segment 91) so that the
individual seal segments can be inserted into the midcompressor
casing 17 The fasteners may be countersunk into the removable cover
43 and positively captured by the rear face of the forward
compressor casing 22. Upon removal of the removable cover 43 access
is provided to the end of a removable seal support 45 within either
casing upper half 87 or within casing lower half 89. The removable
seal support 45 is removably and slidably coupled to midcompressor
casing 17. Access to the removable sealing element is provided
without having to remove the midcompressor casing 17. Forward face
of midcompressor casing 17 may be turned to permit the installation
& removal of removable seal support 45 once access is gained
when the forward compressor casing 22 is removed. The removable
cover 43 is screwed into the midcompressor casing 17 and is
positively captured by the rear face of the forward compressor
casing 22 during normal operation, eliminating any risk of loose
parts causing foreign object damage to the compressor 13.
[0029] The casing assembly 31 enables the replacement of a zero
stage seal assembly 39 without removal of the midcompressor casing
17. The operator can move the zero stage seal assembly 39 by first
removing the forward compressor casing 22. This provides access to
the removable cover 43 which can then be removed to provide access
to the various components of the zero stage seal assembly 39 which
can then be easily removed.
[0030] The terminology used herein is for the purpose of describing
particular embodiments only and is not intended to be limiting of
the invention. Where the definition of terms departs from the
commonly used meaning of the term, applicant intends to utilize the
definitions provided herein, unless specifically indicated. The
singular forms "a", "an" and "the" are intended to include the
plural forms as well, unless the context clearly indicates
otherwise. It will be understood that, although the terms first,
second, etc. may be used to describe various elements, these
elements should not be limited by these terms. These terms are only
used to distinguish one element from another. The term "and/or"
includes any, and all, combinations of one or more of the
associated listed items. The phrases "coupled to" and "coupled
with" contemplates direct or indirect coupling.
[0031] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they have structural elements that do not differ
from the literal language of the claims, or if they include
equivalent structural elements.
* * * * *