Office Action 1: Non-Final Rejection (2025-05-14)
Rejection types: 103 - Obviousness, 112 - Written Description/Enablement

CLAIMS:
CLAIMS

1\. System (21) for sealing and draining leaks of oil for a turbine-engine bearing chamber (E1), this bearing comprising a stator (22) carrying a rotor (23) rotating about a rotation axis (AX), this system (21) comprising a seal (25) carried by the stator (22) and surrounding the
rotor (23), an external circumferential groove (26) carried by the stator (22) while being contiguous with the seal (25) to collect leaking oil (H) travelling along the rotor (23) through the seal (25) and which is centrifuged by the rotor (23) towards this circumferential groove (26), a drain (36) located at the bottom part of the turbine engine for collecting the oil (H) recovered by the circumferential groove (26), this circumferential groove (26) being open towards the rotation axis (AX) while being delimited by a bottom (33) extended by two lateral walls (34, 35), the lateral wall (35) opposite to the seal (25) terminating in a gutter (43) opening towards the bottom (33).

2\. System according to claim 1, wherein the gutter (43) is absent at the bottom part of the
circumferential groove (26).

3\. System according to claim 1, wherein the bottom (33) is formed by a frustoconical wall the inside diameter of which decreases on moving away from the seal (25).

4\. System according to claim 1, comprising an internal circumferential groove (29) formed in the rotor (23) facing the external circumferential groove (26), this internal circumferential groove (29) having a length along the rotation axis (AX) that is less than the length of the external circumferential groove (26) along the rotation axis (AX).

5\. System according to claim 4, wherein the internal circumferential groove (29) has a frustoconically shaped bottom the inside diameter of which decreases on moving away from the seal (25).

6\. System according to claim 3, wherein the rotor includes a circumferential rib (31)
terminating the internal circumferential groove (29).

7\. System according to claim 1, including knife-edge seals (32) secured to the rotor (23) and sliding along a radially internal face of the gutter (43) that is provided with abradable elements, to form a labyrinth seal (42).

8\. Turbine engine comprising a bearing chamber (E1) that is equipped with a sealing system according to claim 1.

9\. Turbine engine comprising a bearing chamber (E1) that is equipped with a sealing system
according to claim 1. 5 10 15 20 25 30

OFFICE ACTION:
DETAILED ACTION
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
Claims 1-9 are currently pending. Claims 1-9 are rejected.
Information Disclosure Statement
The information disclosure statement (IDS) submitted on August 14, 2024 is in compliance with the provisions of 37 CFR 1.97.  Accordingly, the information disclosure statement is being considered by the examiner.
Specification
The abstract of the disclosure is objected to because it contains reference numerals and a reference to Figure 4. Applicant is suggested to remove all references to the drawings.
A corrected abstract of the disclosure is required and must be presented on a separate sheet, apart from any other text. See MPEP § 608.01(b).
Claim Warnings
Applicant is advised that should Claim 8 be found allowable, Claim 9 will be objected to under 37 CFR 1.75 as being a substantial duplicate thereof. When two claims in an application are duplicates or else are so close in content that they both cover the same thing, despite a slight difference in wording, it is proper after allowing one claim to object to the other as being a substantial duplicate of the allowed claim. See MPEP § 608.01(m).
Claim Objections
Claims 1-9 are objected to because of the following informalities:
Regarding Claims 1-9, the preambles of the claims do not contain a grammatical article. Applicant is suggested to add the appropriate grammatical article to the beginning of each claim for grammatical purposes, i.e. “A system” when introducing a system or “The system” when referring to a previously recited system.
Regarding Claim 3, Lines 1-2 recite “formed by a frustoconical wall the inside diameter of which decreases”. This appears to be a run-on. Applicant is suggested to either place proper punctuation to separate appropriate clauses, or reword this.
Regarding Claim 5, Lines 1-2 recite “a frustoconically shaped bottom the inside diameter of which decreases”. This appears to be a run-on. Applicant is suggested to either place proper punctuation to separate appropriate clauses, or reword this.
Appropriate correction is required.
Claim Rejections - 35 USC § 112(b)
The following is a quotation of 35 U.S.C. 112(b):
(b)  CONCLUSION.—The specification shall conclude with one or more claims particularly pointing out and distinctly claiming the subject matter which the inventor or a joint inventor regards as the invention.
Claims 1-9 are rejected under 35 U.S.C. 112(b) or 35 U.S.C. 112 (pre-AIA ), second paragraph, as being indefinite for failing to particularly point out and distinctly claim the subject matter which the inventor or a joint inventor (or for applications subject to pre-AIA  35 U.S.C. 112, the applicant), regards as the invention.
Regarding Claim 1, Line 2 recites “this bearing”. There is insufficient antecedent basis for this limitation in the claim, since a bearing has not been previously recited. It is unclear which bearing the claim refers to. The claim recites a “bearing chamber”, but does not positively recite a bearing. Referring to “this” bearing makes it unclear if a bearing is positively required of the claim or not.
Regarding Claim 1, Lines 3-4 recite “this system comprising a seal carried by the stator and surrounding the rotor”. It is unclear if the stator and rotor are positively required to be a part of the system. Lines 1-2 recite the system is “for a turbine-engine bearing chamber”. There is an issue with the recitation of “this bearing” noted above. However, assuming it is still relating to what the system is being configured “for”, the later recited stator and rotor would not be required of the system. Lines 3-4 are recited in a manner that appears to require the stator and rotor as a part of the system, otherwise the structure of the seal would be indeterminant. Thus, it becomes unclear whether the system is configured for something that comprises a stator carrying a rotor, or if the stator carrying a rotor are a part of the system itself. Note that this issue would persist in all references to the stator and rotor in Claims 1, 4, 6, and 7.
Regarding Claim 1, Line 7 recites “located at the bottom part of the turbine engine”. There is insufficient antecedent basis for this limitation, since neither a bottom part nor a turbine engine has not been previously recited. It is unclear if a turbine engine is required of the system, or if the system merely is configured for a turbine engine.
Regarding Claim 1, Line 10 recites “the lateral wall opposite to the seal”. The scope of the claim requires two lateral walls. It is unclear which lateral wall the claim refers to and what is considered to be “opposite” to the seal. Applicant is reminded that although reference numbers may be used in a claim, they generally do not affect the scope of a claim (MPEP 608.01 (m)). Furthermore, limitations from the Specification, which includes details gleaned from the figures, may not be improperly imported into the claims. The limitation should be reworded such that the intended structure is discernable from the claim language without reliance upon the figures.
Claims 2-9 are subsequently rejected for their dependencies upon a previously rejected claim.
Claim Rejections - 35 USC § 103
In the event the determination of the status of the application as subject to AIA  35 U.S.C. 102 and 103 (or as subject to pre-AIA  35 U.S.C. 102 and 103) is incorrect, any correction of the statutory basis (i.e., changing from AIA  to pre-AIA ) for the rejection will not be considered a new ground of rejection if the prior art relied upon, and the rationale supporting the rejection, would be the same under either status.
The following is a quotation of 35 U.S.C. 103 which forms the basis for all obviousness rejections set forth in this Office action:
A patent for a claimed invention may not be obtained, notwithstanding that the claimed invention is not identically disclosed as set forth in section 102, if the differences between the claimed invention and the prior art are such that the claimed invention as a whole would have been obvious before the effective filing date of the claimed invention to a person having ordinary skill in the art to which the claimed invention pertains. Patentability shall not be negated by the manner in which the invention was made.
The factual inquiries for establishing a background for determining obviousness under 35 U.S.C. 103 are summarized as follows:
1. Determining the scope and contents of the prior art.
2. Ascertaining the differences between the prior art and the claims at issue.
3. Resolving the level of ordinary skill in the pertinent art.
4. Considering objective evidence present in the application indicating obviousness or nonobviousness.
This application currently names joint inventors. In considering patentability of the claims the examiner presumes that the subject matter of the various claims was commonly owned as of the effective filing date of the claimed invention(s) absent any evidence to the contrary.  Applicant is advised of the obligation under 37 CFR 1.56 to point out the inventor and effective filing dates of each claim that was not commonly owned as of the effective filing date of the later invention in order for the examiner to consider the applicability of 35 U.S.C. 102(b)(2)(C) for any potential 35 U.S.C. 102(a)(2) prior art against the later invention.
Claims 1-6 and 8-9, as far as they are definite and understood, are rejected under 35 U.S.C. 103 as being unpatentable over Bordne et al. (US 2013/0283757 A1), hereinafter Bordne, in view of Fang et al. (US 2013/0156547 A1), hereinafter Fang.
Regarding Claim 1, Figures 2-3 of Bordne teach a system for sealing and draining leaks of oil for a turbine-engine (see paragraph [0021]) bearing chamber, this bearing (80) comprising a stator (darker hatched portion in Figure 3) carrying a rotor (lighter hatched portion in Figure 3) rotating about a rotation axis (24), this system comprising a seal (at 80, claim does not specify structure of the seal so anything between two chambers, such as the structure of the bearing assembly, may be considered a seal) carried by the stator and surrounding the rotor, an external circumferential groove (see groove defined by bottom and lateral walls) carried by the stator while being contiguous with the seal (at 80) to collect leaking oil traveling along the rotor through the seal and which is centrifuged by the rotor towards this circumferential groove, this circumferential groove being open towards the rotational axis (24) while being delimited by a bottom extended by two lateral walls, the lateral wall opposite the seal (at 80) terminating in a gutter opening towards the bottom [0030-0033]. Paragraph [0032] discusses the retention of oil for the bearing, one of which would be bearing (80). Oil that contacts the rotor while it is spinning will be centrifuged radially outwards during operation due to physics. Thus, the disclosed structure satisfies the claimed function. See also annotated Figure 2’ below.
PNG
media_image1.png
803
1057
media_image1.png
Greyscale
Bordne does not expressly teach a drain located at the bottom part of the turbine engine for collecting the oil recovered by the circumferential groove as claimed. However, a drain would have been obvious in view of Fang.
Figure 1 of Fang teaches a turbine engine with a drain (where 206 is annotated) located at the bottom part of the turbine engine for collecting the oil recovered by the circumferential groove (radially outer portion of 201). Pressurized oil is used to lubricate the bearing (205). The drain allows for the collection of oil to be pressurized and fed back as a pressurized oil supply [0012-0013].
It would have been obvious to one of ordinary skill in the art before the effective filing date of the claimed invention to modify the system taught by Bordne with a drain located at the bottom part of the turbine engine for collecting the oil recovered by the circumferential groove as suggested by Fang, to provide the benefit of collecting oil so that the oil may be resupplied back to the bearing.
Regarding Claim 2, Bordne and Fang teach the system as set forth in Claim 1.
Figure 2 of Bordne teaches wherein the gutter is absent at the bottom part of the circumferential groove. See annotated Figure 2’ above. The circumferential groove is formed by the lateral walls and bottom part. The “gutter” is interpreted to be the portion not of the bottom part.
Regarding Claim 3, Bordne and Fang teach the system as set forth in Claim 1.
Figures 2-3 of Bordne teach wherein the bottom is formed by a frustoconical wall the inside diameter of which decreases on moving away from the seal (at 80). See also Wall 1 in annotated Figure 3’ below. What is shown in the cross-sections of Figures 2-3 is understood to be revolved around the rotational axis (24).
PNG
media_image2.png
862
1157
media_image2.png
Greyscale
Regarding Claim 4, Bordne and Fang teach the system as set forth in Claim 1.
Figures 2-3 of Bordne teach an internal circumferential groove formed in the rotor (lighter hatched portion in Figure 3) facing the external circumferential groove, this internal circumferential groove having a length along the rotation axis (24) that is less than the length of the external circumferential groove along the rotation axis (24). See also annotated Figures 2’ (external circumferential groove being formed by lateral walls and bottom part) and 3’ above.
Regarding Claim 5, Bordne and Fang teach the system as set forth in Claim 4.
Figures 2-3 of Bordne teach wherein the internal circumferential groove has a frustoconically shaped bottom the inside diameter of which decreases on moving from the seal (at 80). See also annotated Figure 3’ above. The bottom is interpretable as “Wall 2” or any other portion with a decreasing inside diameter.
Regarding Claim 6, Bordne and Fang teach the system as set forth in Claim 3.
Figures 2-3 of Bordne teach wherein the rotor (lighter hatched portion in Figure 3) includes a circumferential rib terminating the internal circumferential groove. See also the right portion of the internal circumferential groove in annotated Figure 3’ above interpreted as a rib.
Regarding Claims 8-9, Bordne and Fang teach the system as set forth in Claim 1.
Figures 1-2 of Bordne teach a turbine engine comprising a bearing chamber (area around bearing assembly 80) that is equipped with a seal system as set forth [0021, 0030-0033].
Claim 7, as far as it is definite and understood, is rejected under 35 U.S.C. 103 as being unpatentable over Bordne and Fang as applied to Claim 1 above, and further in view of Vinski (US 2018/0340439 A1), hereinafter Vinski
Regarding Claim 7, Bordne and Fang teach the system as set forth in Claim 1.
Figures 2-3 of Bordne teach knife edge seals (69) secured to the rotor (lighter hatched portion in Figure 3) and sliding along a radially internal face of the gutter, to form a labyrinth seal (68) [0032, 0041]. See also annotated Figure 2’ above for the gutter.
Bordne and Vinski do not expressly teach the radially internal face of the gutter provided with abradable elements as claimed. However, abradable elements would have been obvious in view of Vinski.
Figure 2 of Vinski teaches a labyrinth seal, where a radially internal face is provided with abradable elements (28). The elements are abradable such that optimization of operating seal clearance occurs. Initial clearance is minimized and then during operation, the knife edge seals (fins) abrade into the abradable elements (seal runner) to create a running clearance, which ensures an optimizes running clearance [0017-0018].
It would have been obvious to one of ordinary skill in the art before the effective filing date of the claimed invention to further modify the system taught by Bordne-Fang such that the radially internal face of the gutter is provided with abradable elements as suggested by Vinski, to provide the benefit of optimizing the running clearance.
Conclusion
The prior art made of record and not relied upon is considered pertinent to applicant's disclosure: Roche et al. (US 2009/0322031 A1) also exemplifies a gutter.


NEXT OFFICE ACTION: DETAILED ACTION
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
Reasons for Allowance
The following is an examiner’s statement of reasons for allowance:
Regarding Claim 1, Applicant’s arguments, see Pg. 7-8 of the response, filed August 14, 2025 are found to be persuasive. In particular, Applicant explains how Bordne et al. (US 2013/0283757 A1) does not expressly teach the claimed seal and groove contiguous to the seal delimited by lateral walls. The amendments also specify the wall positioning as well instead of simply requiring two lateral walls. For instance, the downstream lateral wall is required to be opposite the seal, unlike the sealing at the position of (80) of Bordne is in a relative downstream position of the system interpreted for the claim. The Office agrees with the arguments. Therefore, the rejection of Claim 1 has been withdrawn.
Claims 2-8 and 10-11 subsequently depend upon Claim 1.
Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee.  Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Conclusion

CITED REFERENCE SUMMARIES: Ref US20130283757A1: Claims:
An oil sump seal pressurization apparatus for a turbine engine, the oil sump seal pressurization apparatus comprising: an oil sump comprising at least one bearing mounted therein, the bearing allowing rotation of a shaft with respect to the sump; an oil seal operatively disposed between a non-rotating structural member of the sump and the shaft, the oil sealing having an inward side exposed to an interior of the oil sump and an outward side; a generally radially inwardly oriented passage arranged to supply pressurization air to the outward side of the oil seal; a generally radially outwardly oriented pathway arranged to receive at least some of the pressurization air from the passage, the pathway being at least partially defined by a generally radially outwardly extending arm disposed on the shaft, the arm rotating with the shaft; and a windage shield at least partially separating the passage and the pathway, the windage shield being operatively mounted to the non-rotating structural member of the sump.
an oil sump comprising at least one bearing mounted therein, the bearing allowing rotation of a shaft with respect to the sump;
an oil seal operatively disposed between a non-rotating structural member of the sump and the shaft, the oil sealing having an inward side exposed to an interior of the oil sump and an outward side;
a generally radially inwardly oriented passage arranged to supply pressurization air to the outward side of the oil seal;
a generally radially outwardly oriented pathway arranged to receive at least some of the pressurization air from the passage, the pathway being at least partially defined by a generally radially outwardly extending arm disposed on the shaft, the arm rotating with the shaft; and
a windage shield at least partially separating the passage and the pathway, the windage shield being operatively mounted to the non-rotating structural member of the sump.
The oil sump seal pressurization apparatus of claim 1 , further comprising a pressurization tooth operatively disposed between the passage and the pathway, the pressurization tooth restricting flow of the pressurization air therepast.
The oil sump seal pressurization apparatus of claim 2 , further comprising a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the oil seal, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width; wherein the discourager tooth width is at least about 1.5 times a width of the pressurization tooth.
further comprising a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the oil seal, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width;
wherein the discourager tooth width is at least about 1.5 times a width of the pressurization tooth.
The oil sump seal pressurization apparatus of claim 2 , wherein the pressurization tooth extends radially outwardly from the shaft generally towards the windage shield.
The oil sump seal pressurization apparatus of claim 1 , wherein the windage shield extends generally radially outward with respect to the shaft.
The oil sump seal pressurization apparatus of claim 1 , wherein an air seal is disposed on the arm.
The oil sump seal pressurization apparatus of claim 1 , further comprising a drain arranged to allow draining of oil and venting of at least some of the pressurization air, the drain being positioned axially between the passage and the oil seal; and a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the drain, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width.
a drain arranged to allow draining of oil and venting of at least some of the pressurization air, the drain being positioned axially between the passage and the oil seal; and
a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the drain, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width.
The oil sump seal pressurization apparatus of claim 7 , wherein the discourager tooth width is at least about 2.0 times a width of the pressurization tooth.
The oil sump seal pressurization apparatus of claim 7 , wherein a ratio of discourager tooth width to gap width is greater than about 0.5.
An oil sump seal pressurization apparatus for a turbine engine, the oil sump seal pressurization apparatus comprising a non-rotating oil sump housing a bearing, the bearing supporting a rotatable shaft; an oil seal at least partially isolating an interior of the oil sump, the oil seal operatively acting between a non-rotating structural member of the sump and the rotatable shaft; a passage arranged to supply pressurization air to an outward side of the oil seal with respect to the oil sump; a sump pressurization cavity disposed at least partially around the oil sump, the sump pressurization cavity comprising a volume arranged to supply the pressurization air to the passage; a non-rotatable windage shield disposed within the sump pressurization cavity between the volume and a rotatable arm disposed on the shaft; and a pressurization tooth fluidicly interposing the passage and the rotatable arm, the pressurization tooth restricting flow of the pressurization air from the passage towards the rotatable arm.
a non-rotating oil sump housing a bearing, the bearing supporting a rotatable shaft;
an oil seal at least partially isolating an interior of the oil sump, the oil seal operatively acting between a non-rotating structural member of the sump and the rotatable shaft;
a passage arranged to supply pressurization air to an outward side of the oil seal with respect to the oil sump;
a sump pressurization cavity disposed at least partially around the oil sump, the sump pressurization cavity comprising a volume arranged to supply the pressurization air to the passage;
a non-rotatable windage shield disposed within the sump pressurization cavity between the volume and a rotatable arm disposed on the shaft; and
a pressurization tooth fluidicly interposing the passage and the rotatable arm, the pressurization tooth restricting flow of the pressurization air from the passage towards the rotatable arm.
The oil sump seal pressurization apparatus of claim 10 , wherein the pressurization tooth extends radially outwardly from the shaft generally towards the windage shield.
The oil sump seal pressurization apparatus of claim 10 , wherein the windage shield extends generally radially outward with respect to the shaft.
The oil sump seal pressurization apparatus of claim 10 , wherein an air seal is disposed on the arm.
The oil sump seal pressurization apparatus of claim 10 , further comprising a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the oil seal, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width;
The oil sump seal pressurization apparatus of claim 14 , wherein the discourager tooth width is at least about 1.5 times a width of the pressurization tooth.
An oil sump seal pressurization apparatus for a turbine engine, the oil sump seal pressurization apparatus comprising a non-rotating oil sump housing a bearing, the bearing supporting a rotatable shaft; an oil seal at least partially isolating an interior of the oil sump, the oil seal operatively acting between a non-rotating structural member of the sump and the rotatable shaft; a passage arranged to supply pressurization air to an outward side of the oil seal with respect to the oil sump; a sump pressurization cavity disposed at least partially around the oil sump, the sump pressurization cavity comprising a volume arranged to supply the pressurization air to the passage; a non-rotatable windage shield disposed within the sump pressurization cavity between the volume and a rotatable arm disposed on the shaft; a pressurization tooth fluidicly interposing the passage and the rotatable arm, the pressurization tooth restricting flow of the pressurization air from the passage towards the rotatable arm; and a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the drain, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width; wherein the pressurization tooth extends radially outwardly from the shaft generally towards the windage shield; and wherein the windage shield extends generally radially outward with respect to the shaft.
a non-rotatable windage shield disposed within the sump pressurization cavity between the volume and a rotatable arm disposed on the shaft;
a pressurization tooth fluidicly interposing the passage and the rotatable arm, the pressurization tooth restricting flow of the pressurization air from the passage towards the rotatable arm; and
a discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, the land being disposed axially between the passage and the drain, the discourager tooth being spaced apart from the land in a generally radial direction by a gap having a width, the discourager tooth including an upper surface having a width;
wherein the pressurization tooth extends radially outwardly from the shaft generally towards the windage shield; and
wherein the windage shield extends generally radially outward with respect to the shaft.
The oil sump seal pressurization apparatus of claim 16 , further comprising a drain arranged to allow draining of oil and venting of at least some of the pressurization air, the drain being positioned axially between the passage and the oil seal.
The oil sump seal pressurization apparatus of claim 16 , wherein the discourager tooth width is at least about 1.5 times a width of the pressurization tooth.
The oil sump seal pressurization apparatus of claim 16 , wherein the discourager tooth width is at least about 2.0 times a width of the pressurization tooth.
The oil sump seal pressurization apparatus of claim 16 , wherein the discourager tooth width is at least about 2.5 times a width of the pressurization tooth.
Ref US20130156547A1: Claims:
An eductor for a gas turbine engine comprising: a first zone having a first fluid flow at a first pressure; a second zone having a second fluid flow at a second pressure; a lubrication sump cavity in fluid communication with said first zone and a sump vent; and an eductor valve system having a fluid flow path therethrough in fluid communication with said second zone and said sump vent, and comprising an altitude sensing valve and a gage pressure sensing valve.
a first zone having a first fluid flow at a first pressure;
a second zone having a second fluid flow at a second pressure;
a lubrication sump cavity in fluid communication with said first zone and a sump vent; and
an eductor valve system having a fluid flow path therethrough in fluid communication with said second zone and said sump vent, and comprising an altitude sensing valve and a gage pressure sensing valve.
The eductor for a gas turbine engine of claim 1 , wherein said altitude sensing valve remains open at up to and below an altitude height and remains closed at all other conditions.
The eductor for a gas turbine engine of claim 1 further comprising: an orifice plate in series through said fluid flow path with said gage pressure sensing valve.
an orifice plate in series through said fluid flow path with said gage pressure sensing valve.
The eductor for a gas turbine engine of claim 1 further comprising: a second gage pressure sensing valve in series through said fluid flow path with said altitude sensing valve.
a second gage pressure sensing valve in series through said fluid flow path with said altitude sensing valve.
The eductor for a gas turbine engine of claim 4 , wherein said gage pressure sensing valve remains open at and below a first gage pressure and remains closed at all other conditions.
The eductor for a gas turbine engine of claim 5 , wherein said second gage pressure sensing valve remains open at and below a second gage pressure and remains closed at all other conditions.
The eductor for a gas turbine engine of claim 6 , wherein said first gage pressure is less than or equal to said second gage pressure.
The eductor for a gas turbine engine of claim 4 , wherein said gage pressure sensing valve and said second gage pressure sensing valve react to the gage pressure of said second zone.
An eductor for a gas turbine engine comprising: a first zone having a first fluid flow at a first pressure; a second zone having a second fluid flow at a second pressure; a lubrication sump cavity in fluid communication with said first zone and a sump vent; and an eductor valve system having a fluid flow path therethrough in fluid communication with said second zone and said sump vent, and comprising an altitude sensing valve in parallel through said fluid flow path with a gage pressure sensing valve.
an eductor valve system having a fluid flow path therethrough in fluid communication with said second zone and said sump vent, and comprising an altitude sensing valve in parallel through said fluid flow path with a gage pressure sensing valve.
The eductor for a gas turbine engine of claim 9 , wherein said altitude sensing valve remains open at up to and below an altitude height and remains closed at all other conditions.
The eductor for a gas turbine engine of claim 9 further comprising: an orifice restrictor plate in series with said gage pressure sensing valve.
an orifice restrictor plate in series with said gage pressure sensing valve.
The eductor for a gas turbine engine of claim 9 further comprising: a second gage pressure sensing valve in series through said fluid flow path with said altitude sensing valve.
The eductor for a gas turbine engine of claim 9 , wherein said gage pressure sensing valve remains open at and below a first gage pressure of said second zone and remains closed at all other conditions.
The eductor for a gas turbine engine of claim 13 further comprising: a second gage pressure sensing valve in series through said fluid flow path with said altitude sensing valve; wherein said second gage pressure sensing valve remains open and below a second gage pressure of said second zone and remains closed at all other conditions.
a second gage pressure sensing valve in series through said fluid flow path with said altitude sensing valve;
wherein said second gage pressure sensing valve remains open and below a second gage pressure of said second zone and remains closed at all other conditions.
The eductor for a gas turbine engine of claim 14 , wherein said first gage pressure is different than said second gage pressure.
The eductor for a gas turbine engine of claim 14 , wherein said first gage pressure is less than or equal to said second gage pressure.
The eductor for a gas turbine engine of claim 14 further comprising a nozzle in fluid communication with said lubrication sump cavity through said sump vent and a vent tube.
An apparatus comprising: a gas turbine engine having a low pressure compressor zone and a high pressure compressor zone; said low pressure compressor zone having a fluid flow at a first pressure corresponding to a power output of said engine; said high pressure compressor zone having a fluid flow at a second pressure corresponding to said power output of said engine; a lubrication sump cavity in fluid communication with said low pressure compressor zone and a sump cavity vent; and an eductor valve system having a fluid flow path therethrough in fluid communication with said high pressure compressor zone and said sump vent, and comprising an altitude sensing valve, a first gage pressure sensing valve, and a second gage pressure sensing valve; wherein said altitude sensing valve is in parallel through said fluid flow path with said first gage pressure sensing valve; and wherein said altitude sensing valve is in series through said fluid flow path with said second gage pressure sensing valve.
a gas turbine engine having a low pressure compressor zone and a high pressure compressor zone;
said low pressure compressor zone having a fluid flow at a first pressure corresponding to a power output of said engine;
said high pressure compressor zone having a fluid flow at a second pressure corresponding to said power output of said engine;
a lubrication sump cavity in fluid communication with said low pressure compressor zone and a sump cavity vent; and
an eductor valve system having a fluid flow path therethrough in fluid communication with said high pressure compressor zone and said sump vent, and comprising an altitude sensing valve, a first gage pressure sensing valve, and a second gage pressure sensing valve;
wherein said altitude sensing valve is in parallel through said fluid flow path with said first gage pressure sensing valve; and
wherein said altitude sensing valve is in series through said fluid flow path with said second gage pressure sensing valve.
The apparatus of claim 18 , wherein said first gage pressure sensing valve and said second gage pressure sensing valve react to the gage pressure of said second zone.
The apparatus of claim 18 further comprising an orifice restrictor in series through said fluid flow path with said first gage pressure sensing valve.
Ref US20180340439A1: Claims:
A seal assembly for a turbine engine having a shaft with a rotary axis and a housing surrounding the shaft; the seal assembly being disposed between the shaft and the housing, the seal assembly comprising: an outer labyrinth seal having multiple outer fins in opposing sealing engagement with a concentric outer seal runner, one of: the outer labyrinth seal fins; and the outer seal runner, engaging the housing, and the shaft engaging an opposing one of: the outer seal runner; and the outer labyrinth seal fins; an inner labyrinth seal, disposed radially inwardly concentric to and axially overlapping the outer labyrinth seal and the outer seal runner, the inner labyrinth seal having multiple inner fins in opposing sealing engagement with a concentric inner seal runner, one of: the inner labyrinth seal fins; and the inner seal runner, engaging the housing, and the shaft engaging an opposing one of: the inner seal runner; and the inner labyrinth seal fins; and an intermediate plenum, defined between the outer fins, the inner fins, the housing and the shaft, the intermediate plenum in communication with a source of compressed gas having a supply pressure greater than an ambient pressure external to the housing and greater than an internal pressure within the housing.
an outer labyrinth seal having multiple outer fins in opposing sealing engagement with a concentric outer seal runner, one of: the outer labyrinth seal fins; and the outer seal runner, engaging the housing, and the shaft engaging an opposing one of: the outer seal runner; and the outer labyrinth seal fins;
an inner labyrinth seal, disposed radially inwardly concentric to
[Truncated to input limit]